CN212111801U - Civil aviation big dipper navigation antenna - Google Patents
Civil aviation big dipper navigation antenna Download PDFInfo
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- CN212111801U CN212111801U CN202020231510.0U CN202020231510U CN212111801U CN 212111801 U CN212111801 U CN 212111801U CN 202020231510 U CN202020231510 U CN 202020231510U CN 212111801 U CN212111801 U CN 212111801U
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- frequency point
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- point receiving
- receiving link
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Abstract
The utility model discloses a civil aviation Beidou navigation antenna, which comprises an S frequency point receiving link, a B1 frequency point receiving link and a B2 frequency point receiving link; the S frequency point receiving link, the B1 frequency point receiving link and the B2 frequency point receiving link are all electrically connected with a combined link, and the combined link is electrically connected with a wire-through socket and a transmitting link; the S frequency point receiving link, the B1 frequency point receiving link, the B2 frequency point receiving link, the combining link and the transmitting link are all installed in the lightning protection radome, and the all-wire socket is installed at the bottom of the lightning protection radome. The utility model is structurally designed in a compact and ultra-thin type, and the electric units with different functions such as a power DC-DC booster circuit, a power amplification circuit, a control circuit and the like are isolated from each other in a cavity-divided manner, so that the electromagnetic radiation units are ensured not to interfere with each other; the heat dissipation device improves the mechanical resistance through the partition plate, ensures the impact resistance, realizes the uniform distribution and heat dissipation of a heat source, controls the temperature rise, and ensures the junction temperature of electronic components.
Description
Technical Field
The utility model belongs to the electricity field especially relates to a civil aviation big dipper navigation antenna.
Background
Because the current civil aircraft is provided with a GPS antenna, a GPS navigation system does not support reporting of position information. After the civil aircraft breaks down, the search and rescue range of the aviation equipment cannot be confirmed, which brings disadvantages to the search and rescue work and loses the best search and rescue opportunity, such as a horse navigation event. And the Beidou navigation system in China can support the function, so that the civil aircraft needs an antenna supporting the Beidou navigation system.
Except that in addition, civil aircraft all works at the high altitude, wears cloud layer or weather sudden change and can bring the thunderbolt phenomenon, in order to prevent the thunderbolt, big dipper antenna need carry out lightning protection, can adopt water conservancy diversion strip and external lightning protection ware, but the water conservancy diversion strip can influence the gain of antenna element and worsen the fire resistance of antenna, and external lightning protection ware is inconvenient when installation and use.
The civil aircraft uses a GPS navigation system as a navigation system at present, so that the antenna of the modified civil aircraft cannot influence the GPS navigation system of the original aircraft, which is the premise of adding the modified antenna. The civil aircraft works at high altitude, and effective fire fighting can not be carried out through external resources in case of fire, so that the design of the whole antenna is fire-retardant and the fire-retardant requirement of the civil aircraft is required to be met.
The noun explains:
LNA: a Low Noise Amplifier.
PA: power Amplifier Power Amplifier.
RDSS: radio Determination Satellite Radio Service.
RNSS: a Radio Navigation Satellite Radio Navigation Service. BDS BeiDou Navigation Satellite System.
SUMMERY OF THE UTILITY MODEL
In order to solve the problem, the utility model provides a civil aviation big dipper navigation antenna. The utility model discloses acquire the positional information of current airborne vehicle through BDS's RNSS function, report to the commander on ground through BDS's RDSS function after packing this information, return the positional information of airborne vehicle back to ground, realized the position tracking function of civilian airborne vehicle; the lightning protection function is added, the performance and the flame retardant effect of the original GPS antenna are not affected, the normal work of a nearby GPS system is not affected during working, and the lightning protection is not required to be carried out through additional auxiliary equipment.
In order to achieve the above technical effects, the technical scheme of the utility model is that:
a civil aviation Beidou navigation antenna comprises an S frequency point receiving link, a B1 frequency point receiving link and a B2 frequency point receiving link; the S frequency point receiving link, the B1 frequency point receiving link and the B2 frequency point receiving link are all electrically connected with a combined link, and the combined link is electrically connected with a cable socket 1 and a transmitting link; the S frequency point receiving link, the B1 frequency point receiving link, the B2 frequency point receiving link, the combining link and the transmitting link are all installed in the lightning protection antenna cover, and the all-in-one socket 1 is installed on the lightning protection antenna cover.
In a further improvement, the lightning protection radome is a polyether-ether-ketone radome body, and the thickness of the lightning protection radome body is 3 mm.
In a further improvement, the S frequency point receiving link comprises an S oscillator and a low noise amplifier of an S frequency point, the B1 frequency point receiving link comprises a B1 oscillator and a low noise amplifier of a B1 frequency point, and the B2 frequency point receiving link comprises a B2 oscillator and a low noise amplifier of a B2 frequency point; the transmitting link comprises an L oscillator and a power amplifier of an L frequency point; the S oscillator, the B1 oscillator, the L oscillator and the B2 oscillator are respectively and electrically connected with a GDT ceramic discharge tube first induction lightning protection circuit, a GDT ceramic discharge tube second induction lightning protection circuit and a GDT ceramic discharge tube third induction lightning protection circuit, the GDT ceramic discharge tube first induction lightning protection circuit comprises a GDT ceramic discharge tube, the GDT ceramic discharge tube first induction lightning protection circuit is electrically connected with a first capacitor C1, the first capacitor C1 is electrically connected with a dielectric filter U1, the dielectric filter U1 is electrically connected with a first diode D1 and a first low noise amplifier LNA1, the first low noise amplifier LNA1 is electrically connected with a low noise amplifier GRF 2051U 2, the low noise amplifier GRF 2051U 2 is electrically connected with a second low noise amplifier LNA2, and the second low noise amplifier LNA2 is electrically connected with a first resistor R1; the first resistors R1 of the B1 frequency point receiving link and the B2 frequency point receiving link are directly and electrically connected with the combining link; the S-frequency receiving link is electrically connected to the combining link through a third low noise amplifier LNA 3.
In a further improvement, the combining link comprises a two-power divider GP2S1+ U3 electrically connected with a B1 frequency point receiving link and a B2 frequency point receiving link, the two-power divider GP2S1+ U3 is electrically connected with a fourth low noise amplifier LNA4, the fourth low noise amplifier LNA4 is electrically connected with a single chip amplifier SPF5043ZU4, and the single chip amplifier SPF5043ZU4 is electrically connected with a transmitting link and a duplexer DP2012U 5; the duplexer DP2012U5 is electrically connected with the S frequency point receiving link and a second resistor R2, the second resistor R2 is electrically connected with a second capacitor C2, the second capacitor C2 is electrically connected with a GDT ceramic discharge tube, a second inductive lightning protection circuit and a first inductive coil L1, and the second inductive lightning protection circuit is electrically connected with a wire-through socket 1; the first induction coil L1 is electrically connected with the third capacitor C3, the second diode D2 and the third diode D3; the second inductive lightning protection circuit of the GDT ceramic discharge tube is the same as the first inductive lightning protection circuit of the GDT ceramic discharge tube.
In a further improvement, the transmitting link comprises a sound meter filter TA0528AU8, the sound meter filter TA0528AU8 is electrically connected with a monolithic amplifier YG602020PA2, the monolithic amplifier YG602020 is electrically connected with a third resistor R3, the third resistor R3 is electrically connected with a monolithic amplifier SPF5043Z PA1, the monolithic amplifier SPF5043Z PA1 is electrically connected with an LDMOS power tube BLF6G21-10GLDMOS1, the LDMOS power tube BLF6G21-10GLDMOS1 is electrically connected with a two power divider GP2S1+ U7, the two power dividers GP2S1+ U7 are electrically connected with a power amplifier U6 of an L frequency point, the power amplifier U6 of the L frequency point is electrically connected with a GDT ceramic discharge tube third inductive lightning protection circuit through a fourth capacitor C4, and the GDT ceramic discharge tube third inductive lightning protection circuit is electrically connected with the L oscillator.
The utility model has the advantages that:
1. the method comprises the steps of obtaining the position information of the current aircraft through the RNSS function of the BDS, packaging the information, reporting the information to the command department of the bottom surface through the RDSS function of the BDS, transmitting the position information of the aircraft back to the bottom surface, and achieving the tracking function.
2. The lightning protection function is added, the original GPS function and the flame retardant effect are not affected, the normal work of a nearby GPS system is not affected during working, and the lightning protection is not required to be carried out through additional auxiliary equipment.
Drawings
Fig. 1 is a schematic view of the overall structure of the present invention;
fig. 2 is a schematic structural diagram of a lightning protection radome;
fig. 3 is a functional block diagram of an S-frequency receiving link;
fig. 4 is a functional block diagram of a B1 frequency point receiving link;
fig. 5 is a functional block diagram of a B2 frequency point receiving link;
fig. 6 is a functional block diagram of a combining link;
fig. 7 is a functional block diagram of a transmit chain.
Detailed Description
The technical solution of the present invention will be described in detail with reference to the following embodiments and accompanying drawings.
Example 1
The utility model discloses an antenna improves on the navigation communication antenna equipment basis on ground, satisfies the service environment of airborne vehicle through improving multinomial parameter. The technical implementation scheme is as follows: there are mainly three functional units: the antenna comprises an S oscillator, a B1 oscillator, a B2 oscillator and an L oscillator, wherein the antenna oscillator is connected with a structural member (a lightning protection antenna housing and a wire-through socket 1) through an active module. The antenna oscillator and the active module are connected through the MCX connector, and the structural member provides a stable working environment for the active module and the antenna oscillator. The antenna adopts a wire harness-in design, an electric signal transmitting signal flows to the antenna from a cable, a receiving signal flows to the cable from the antenna, the antenna acquires tracking equipment position information through a B1I frequency point of BDS, a receiver packs the position information and judges the state of a navigation satellite through an S frequency point, and under the effective condition of the S frequency point, the position information is transmitted to a specified ID number through an L frequency point, so that the position reporting function of a navigator is realized.
Structural design: the most key factors of ensuring the stable environment of the active module and the antenna oscillator, direct lightning protection and environmental adaptability are realized.
Active module design: the low-noise power amplifier completes the functions of low-noise amplification, power amplification and filtering of navigation signals, has the function of direct/indirect lightning stroke protection, realizes the starting function of the power amplifier by detecting input voltage, and is a key element of electromagnetic compatibility.
Designing an antenna element: the electromagnetic wave conversion function of the free space of the multi-frequency point signal of the Beidou navigation signal and the transmission line is realized.
The structural design of protection product, the material of lightning protection antenna house is PEEK, and thickness 3mm can realize the direct thunderbolt protect function of antenna
The above-mentioned is only a concrete direction embodiment of the utility model, nevertheless the utility model discloses a design concept is not limited to this, and all utilize this design right the utility model discloses carry out immaterial change, all should belong to the action of infringing the scope of protection of the utility model.
Claims (5)
1. A civil aviation Beidou navigation antenna is characterized by comprising an S frequency point receiving link, a B1 frequency point receiving link and a B2 frequency point receiving link; the S frequency point receiving link, the B1 frequency point receiving link and the B2 frequency point receiving link are all electrically connected with a combined link, and the combined link is electrically connected with a wire-through socket (1) and a transmitting link; the S frequency point receiving link, the B1 frequency point receiving link, the B2 frequency point receiving link, the combining link and the transmitting link are all installed in the lightning protection antenna cover, and the all-in-one socket (1) is installed on the lightning protection antenna cover.
2. The civil aviation Beidou navigation system antenna of claim 1, wherein the lightning protection radome is a polyetheretherketone radome body and has a thickness of 3 mm.
3. The civil aviation Beidou navigation antenna according to claim 1, wherein the S frequency point receiving link comprises an S oscillator and a low noise amplifier of an S frequency point, the B1 frequency point receiving link comprises a B1 oscillator and a B1 frequency point low noise amplifier, and the B2 frequency point receiving link comprises a B2 oscillator and a B2 frequency point low noise amplifier; the transmitting link comprises an L oscillator and a power amplifier of an L frequency point; the S oscillator, the B1 oscillator, the L oscillator and the B2 oscillator are electrically connected with a GDT ceramic discharge tube first induction lightning protection circuit, a GDT ceramic discharge tube second induction lightning protection circuit and a GDT ceramic discharge tube third induction lightning protection circuit respectively, the GDT ceramic discharge tube first induction lightning protection circuit comprises a GDT ceramic discharge tube, the GDT ceramic discharge tube first induction lightning protection circuit is electrically connected with a first capacitor (C1), the first capacitor (C1) is electrically connected with a dielectric filter (U1), the dielectric filter (U1) is electrically connected with a first diode (D1) and a first low noise amplifier (LNA1), the first low noise amplifier (LNA1) is electrically connected with a low noise amplifier GRF2051(U2), the low noise amplifier GRF2051(U2) is electrically connected with a second low noise amplifier (LNA2), and the second low noise amplifier (LNA2) is electrically connected with a first resistor (R1); the first resistors (R1) of the B1 frequency point receiving link and the B2 frequency point receiving link are directly and electrically connected with the combining link; the S-frequency point receiving link is electrically connected with the combining link through a third low noise amplifier (LNA 3).
4. The civil aviation Beidou navigation antenna according to claim 1, wherein the combining link comprises a two-power divider GP2S1+ (U3) electrically connected with a B1 frequency point receiving link and a B2 frequency point receiving link, the two-power divider GP2S1+ (U3) is electrically connected with a fourth low noise amplifier (LNA4), the fourth low noise amplifier (LNA4) is electrically connected with a single chip amplifier SPF5043Z (U4), and the single chip amplifier SPF5043Z (U4) is electrically connected with a transmitting link and a duplexer DP2012 (U5); the duplexer DP2012(U5) is electrically connected with the S frequency point receiving link and a second resistor (R2), the second resistor (R2) is electrically connected with a second capacitor (C2), the second capacitor (C2) is electrically connected with a GDT ceramic discharge tube, a second inductive lightning protection circuit and a first inductive coil (L1), and the second inductive lightning protection circuit is electrically connected with a wire-through socket (1); the first induction coil (L1) is electrically connected with the third capacitor (C3), the second diode (D2) and the third diode (D3); the second inductive lightning protection circuit of the GDT ceramic discharge tube is the same as the first inductive lightning protection circuit of the GDT ceramic discharge tube.
5. The civil aviation Beidou navigation system antenna of claim 1, wherein the transmitting link comprises a sound meter filter TA0528A (U8), the sound meter filter TA052 0528A (U8) is electrically connected with a monolithic amplifier YG602020(PA2), the monolithic amplifier YG602020 is electrically connected with a third resistor (R3), the third resistor (R3) is electrically connected with a monolithic amplifier SPF5043Z (PA1), the monolithic amplifier SPF5043Z (PA1) is electrically connected with an LDMOS power tube BLF6G21-10G (LDMOS1), the LDMOS power tube BLF6G21-10G (LDMOS1) is electrically connected with a second power divider GP2S1+ (U7), the second power divider GP2S1+ (U7) is electrically connected with a power amplifier (U6) of L, the power amplifier (U6) of L is electrically connected with a GDT ceramic discharge tube through a fourth capacitor (C4), and the third inductive lightning protection circuit is electrically connected with a lightning frequency point protection circuit.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020231510.0U CN212111801U (en) | 2020-02-28 | 2020-02-28 | Civil aviation big dipper navigation antenna |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020231510.0U CN212111801U (en) | 2020-02-28 | 2020-02-28 | Civil aviation big dipper navigation antenna |
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| Publication Number | Publication Date |
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| CN212111801U true CN212111801U (en) | 2020-12-08 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202020231510.0U Active CN212111801U (en) | 2020-02-28 | 2020-02-28 | Civil aviation big dipper navigation antenna |
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| CN (1) | CN212111801U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113097749A (en) * | 2021-03-24 | 2021-07-09 | 河北晶禾电子技术股份有限公司 | Four-system high-precision navigation antenna |
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2020
- 2020-02-28 CN CN202020231510.0U patent/CN212111801U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113097749A (en) * | 2021-03-24 | 2021-07-09 | 河北晶禾电子技术股份有限公司 | Four-system high-precision navigation antenna |
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