CN204422747U - Helicopter-guiding system self-checking coded transmitter - Google Patents
Helicopter-guiding system self-checking coded transmitter Download PDFInfo
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- CN204422747U CN204422747U CN201420807060.XU CN201420807060U CN204422747U CN 204422747 U CN204422747 U CN 204422747U CN 201420807060 U CN201420807060 U CN 201420807060U CN 204422747 U CN204422747 U CN 204422747U
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- radar
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- dielectric resonator
- guiding system
- resonator oscillator
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Abstract
The utility model discloses a kind of helicopter-guiding system self-checking coded transmitter, comprise dielectric resonator oscillator, PIN modulator, attenuator, microstrip antenna and answer signal coding circuit, described dielectric resonator oscillator produces radiofrequency signal, answer signal coding circuit detects radar bow simultaneously, after orientation and trigger pip, the pulse code signal of certain time-delay is produced at particular orientation place, this pulse code signal is sent to described PIN modulator, and then control described PIN modulator radio frequency signal and carry out switch modulation, with the radio-frequency pulse of coded message after modulation, through described attenuator attenuates, finally by described microstrip antenna to external radiation, if radio-frequency pulse receives after process through radar antenna and normally shows on radar terminal processes and displays equipment after decay, then prove that guidance system is working properly.The utility model can be installed in navar servo unit, and carry out real-time self-inspection to the performance of helicopter-guiding system, volume is little, cost is low.
Description
Technical field
The utility model relates to a kind of self-inspection, testing apparatus, more particularly a kind of helicopter-guiding system self-checking coded transmitter.
Background technology
Ship-borne helicopter is anticipated the helicopter namely used on boats and ships.Along with the development of shipping scale grows, increasing large vessel is equipped with ship-borne helicopter.
Navigation peculiar to vessel helicopter-guiding radar system of holding concurrently is a kind of economical and practical helicopter-guiding system, and it is made up of marine navigation radar system and airborne transponder two part.As shown in Figure 1, for navigation peculiar to vessel is held concurrently helicopter-guiding radar system operating diagram.Marine navigation radar system comprises radar antenna 2, and this radar antenna 2 is arranged on the marine radar gear case of navar servo unit 3 inside, this marine radar gear case built with one for driving the motor of radar antenna 2.Navar servo unit 3 connects radar terminal processes and displays equipment 5 by waveguide 4.Navigation radar system sends the interrogating signal of specific pulsewidth to airborne transponder 1, after airborne transponder 1 receives, navigation radar system beams back the pulse code signal with helicopter information, navigation radar system carries out identifying processing after receiving pulse code signal by radar antenna 2, on radar terminal processes and displays equipment 5, finally show aircraft-position information and other relevant informations, guarantee that ship-borne helicopter makes a return voyage after executing the task on boundless sea smoothly.
Because the performance quality of helicopter-guiding system is directly connected to the life security of aircrew and the device security of helicopter, so effective self-inspection must be carried out to guidance system, confirm that its duty is normal.As shown in Figure 2, the method of currently used helicopter-guiding System self-test is summarized as follows: select place's plateau apart from the far place (more than 30km) of ship, erection airborne transponder 1, helicopter simulating guidance system operative scenario, detects whole guidance system.
But there is following shortcoming in this self checking method:
(1) airborne transponder volume is large, heavy, not Portable belt;
(2) for simulation long-distance flight helicopter and avoid signal to block, airborne transponder need be set up in apart from the comparatively far away and position of certain altitude of radar, addressing difficulty;
(3) when boat trip, System self-test cannot be guided in real time;
(4) airborne transponder is expensive, and addressing is measured, and human cost is high.
Utility model content
The purpose of this utility model is to provide a kind of helicopter-guiding system self-checking coded transmitter, can directly be installed in marine navigation radar servo unit, real-time self-inspection is carried out to the performance of helicopter-guiding system, thus overcomes that airborne transponder volume is large, self-inspection addressing difficulty, human cost are high and cannot the shortcoming of self-inspection in real time.
The utility model is achieved through the following technical solutions:
Helicopter-guiding system self-checking coded transmitter, to be installed in a marine navigation radar servo unit and to use with marine navigation radar system support, this transmitter comprises dielectric resonator oscillator, PIN modulator, attenuator, microstrip antenna and answer signal coding circuit, described dielectric resonator oscillator, isolator, PIN modulator, attenuator is fixedly connected sequentially into a structure, one end of described attenuator connects one end that a waveguide turns coaxial converter, the other end that this waveguide turns coaxial converter connects described microstrip antenna, described answer signal coding circuit is fixedly connected on the top of described structure by a support member, the bottom of described structure is provided with a fixed support, this fixed support is fixed in described marine navigation radar servo unit.
Further, described dielectric resonator oscillator produces radiofrequency signal, answer signal coding circuit detects radar bow simultaneously, after orientation and trigger pip, the pulse code signal of certain time-delay is produced at particular orientation place, this pulse code signal is sent to described PIN modulator, and then control described PIN modulator radio frequency signal and carry out switch modulation, with the radio-frequency pulse of coded message after modulation, decay through described attenuator, finally by described microstrip antenna to external radiation, normally show on radar terminal processes and displays equipment if the radio-frequency pulse after decay receives after process through radar antenna, then prove that helicopter-guiding system works is normal.
Further, described answer signal coding circuit is fixedly connected on the top of described dielectric resonator oscillator by a support member.
Further, the bottom of described attenuator, dielectric resonator oscillator is respectively equipped with described fixed support.
Further, between described dielectric resonator oscillator and described PIN modulator, being provided with an isolator, for isolating the impact of described PIN modulator sending-end impedance change on described dielectric resonator oscillator, guaranteeing that dielectric resonator oscillator output frequency is stablized.
Further, described attenuator adopts variable attenuator, for regulating radio frequency encoding pulse output power, thus simulates the helicopter RF encoded signal returned at a distance.
Further, described dielectric resonator oscillator uses field effect transistor as active device.
Further, described PIN modulator is combined by two PIN switching diodes and waveguide.
Further, described answer signal coding circuit produces the pulse code signal controlling described PIN modulator.
Further, described microstrip antenna is by radiation element, dielectric layer and form with reference to ground three parts, and described microstrip antenna adopts coaxial feeding mode.
Further, described marine navigation radar servo unit comprises a marine radar gear case, and this marine radar gear case is built-in with a motor, and described radar antenna is arranged at above described marine radar gear case, and described motor is for driving described radar antenna.
Further, described dielectric resonator oscillator, PIN modulator, attenuator, microstrip antenna and answer signal coding circuit are all arranged in described marine radar gear case, this marine radar gear case is provided with opening, and described microstrip antenna is close to described opening inner side place.
Further, described marine navigation radar system comprises navar servo unit, radar antenna, waveguide, radar terminal display.
Beneficial effect: the utility model helicopter-guiding system self-checking coded transmitter, main in order to simulate the encoding the response signal that airborne transponder is beamed back, directly can be installed in marine navigation radar servo unit, real-time self-inspection is carried out to the performance of helicopter-guiding system.Volume is little, cost is low.Thus it is large to overcome existing airborne transponder volume, self-inspection addressing difficulty, human cost is high, cannot the shortcoming of self-inspection in real time.
Accompanying drawing explanation
Fig. 1 is the double helicopter-guiding radar system block diagram of navigation.
Fig. 2 is currently used guidance system self-inspection block diagram.
Fig. 3 is the system works block diagram of the utility model self-checking coded transmitter.
Fig. 4 is the installation site figure of the utility model self-checking coded transmitter.
In Fig. 5:
5a is microstrip antenna HFSS realistic model figure in the utility model.
5b is microstrip antenna standing wave ratio of input voltage simulation result in the utility model.
5c is microstrip antenna radiation pattern simulation result in the utility model.
Fig. 6 is the surface structure schematic diagram of the utility model self-checking coded transmitter.
When Fig. 7 is the utility model helicopter-guiding System self-test, at the helicopter Test code signal graph that radar terminal normally shows.
Each symbol in figure: 1. airborne transponder, 2. radar antenna, 3. navar servo unit, 4. waveguide, 5. radar terminal processes and displays equipment, 6. self-checking coded transmitter, 7. fixed support, 8. answer signal coding circuit, 9. microstrip antenna, 10. support member, 11. waveguides turn coaxial converter, 12. attenuators, 13.PIN modulator, 14. isolators, 15. dielectric resonator oscillators.
Embodiment
Below in conjunction with accompanying drawing, embodiment of the present utility model is elaborated: the present embodiment is implemented under premised on technical solutions of the utility model; give detailed embodiment and concrete operating process, but protection domain of the present utility model is not limited to following embodiment.
Embodiment:
See Fig. 3, Fig. 4, Fig. 6, self-checking coded transmitter 6 is made up of dielectric resonator oscillator 15, PIN modulator 13, attenuator 12, microstrip antenna 9 and answer signal coding circuit 8 five part.Self-checking coded transmitter 6 is installed in marine radar gear case, is the ingredient of navar servo unit 3 in marine radar gear case.Attenuator 12 adopts variable attenuator, for regulating RF encoded signal output power.Isolator 14 is located between dielectric resonator oscillator 15 and PIN modulator 13, for isolating the impact of PIN modulator 13 sending-end impedance change on dielectric resonator oscillator 15, guarantees that dielectric resonator oscillator 15 output frequency is stablized.One end that waveguide turns coaxial converter 11 is connected on attenuator 12, and the other end that waveguide turns coaxial converter 11 connects microstrip antenna 9.Waveguide turns coaxial converter 11 and the output of waveguide square opening is changed into coaxial round mouth.
Dielectric resonator oscillator 15, isolator 14, PIN modulator 13 are fixedly connected sequentially into a structure with attenuator 12 in marine radar gear case.Marine radar gear case is provided with opening, and this opening is positioned at above microstrip antenna 9, by above-mentioned opening, and microstrip antenna 9 externally radiation signal.Answer signal coding circuit 8 is fixedly connected on the top of structure by support member 10, and the bottom of structure is provided with fixed support 7, and this fixed support 7 is fixed in marine navigation radar servo unit.
For signal 111111: dielectric resonator oscillator 15 produces radiofrequency signal, answer signal coding circuit 8 detects radar bow simultaneously, after orientation and trigger pip, the pulse code signal of certain time-delay is produced at particular orientation place, this pulse code signal is sent to described PIN modulator 13, and then control described PIN modulator 13 radio frequency signal and carry out switch modulation, with the radio-frequency pulse of " 111111 " self-checking coded message after modulation, decay through described attenuator 12, finally by microstrip antenna 9 to external radiation, after radio-frequency pulse after decay is received by radar antenna 2, radar terminal processes and displays equipment 5 is entered by Radar Servo unit 3 and waveguide 4, " 111111 " the radio frequency encoding pulse received becomes coded signal in radar terminal processes and displays equipment 5 after detection process, finally normally show on radarscope, prove that helicopter-guiding system works is normal.
Dielectric resonator oscillator 15 uses field effect transistor as active device.After selecting suitable quiescent point, field effect transistor works in negative resistance state, the selecting frequency characteristic of binding medium resonant cavity, meets starting condition for oscillation at characteristic frequency point, thus produces specific strength frequency.It is good that dielectric resonator oscillator 15 has frequency stability as radio-frequency signal source, the advantage that cost is low.
PIN modulator 13 is combined by two PIN switching diodes and waveguide.It utilizes PIN diode under the positive and negative bias voltage of direct current, present the approximate impedance operator be turned on or off, and achieves the control of radio frequency signal conduction or cut-off, thus can carry out switch modulation to the radiofrequency signal that oscillator exports.
Answer signal coding circuit 8 is for generation of the pulse code signal of control PIN modulator 13.Encoding the response circuit 8 uses FPGA (field programmable gate array) to detect bow, orientation and trigger pip, start to count bearing signal after it detects bow, export pulse code signal at particular orientation place, thus ensure that the stability of pulse code signal in orientation.In addition, the coded signal that middle helicopter beams back is moved in order to simulate distant location, answer signal coding circuit 8 pairs of trigger pips also detect, pulse code signal is changed relative to trigger pip time delay (time delay from large to small) by FPGA, achieve coded signal to move, simulate the flight course that helicopter draws near.
See Fig. 5, microstrip antenna is by radiation element, dielectric layer and form with reference to ground three parts, and helicopter-guiding System self-test Test code transmitter adopts microstrip antenna, and it is light that microstrip antenna has quality, and volume is little, the low feature with being convenient to manufacture of cost.The parameter relevant to antenna performance mainly comprises length L, the width W of radiation element, the thickness h of dielectric layer, the relative dielectric constant ε of medium of radiation element
rwith tan δ etc.Self-checking coded transmitter microstrip antenna used is based on coaxial feed mode, internal core wire by coaxial cable joint is connected with radiation element with dielectric layer through reference point, dielectric material used is copper foil clad plate of polytetrafluoroethylglass glass cloth, and specific inductive capacity is 2.2, and dielectric thickness is 1mm.On the basis of theory calculate microstrip antenna length and width numerical value and feed placement, use HFSS software to carry out design optimization again to these numerical value, thus obtain best antenna Input matching and antenna radiation characteristics.Fig. 5 a is the realistic model of microstrip antenna HFSS, and microstrip antenna adopts probe feed form.Fig. 5 b is microstrip antenna standing wave ratio of input voltage simulation result, and voltage standing wave ratio (VSWR) has reacted microstrip antenna incoming feeder terminal impedance matching degree, and voltage standing wave ratio (VSWR) is more close to 1, then microstrip antenna Input matching is better, and antenna gain is also higher.As the long 9.73mm of microstrip antenna, width is 12.73mm, when feed position is apart from center 2.1mm, from figure m1 point place, is 1.029 in 9.41GHz place voltage standing wave ratio (VSWR).Fig. 5 c is the simulation result of antenna pattern, and as seen from the figure, the antenna gain of microstrip antenna on 0 degree of direction can reach 5dB.
See Fig. 7, be (such as: " 111111 " coded signal launched by self-checking code transmitter) during the utility model helicopter-guiding System self-test, the helicopter Test code signal graph of normal display on radar terminal display interface.In figure, border circular areas is radar return display circle, and in border circular areas, each bright spot all represents " 1 " signal, can find out that " 111111 " coded signal launched by self-checking code transmitter can clear display on radar terminal processes and displays equipment.
More than show and describe ultimate principle of the present utility model and principal character and advantage of the present utility model.The technician of the industry should understand; the utility model is not restricted to the described embodiments; what describe in above-described embodiment and instructions just illustrates principle of the present utility model; under the prerequisite not departing from the utility model spirit and scope; the utility model also has various changes and modifications, and these changes and improvements all fall within the scope of claimed the utility model.The claimed scope of the utility model is defined by appending claims and equivalent thereof.
Claims (9)
1. helicopter-guiding system self-checking coded transmitter, it is characterized in that, to be installed in a marine navigation radar servo unit and to use with marine navigation radar system support, this transmitter comprises dielectric resonator oscillator, PIN modulator, attenuator, microstrip antenna and answer signal coding circuit, described dielectric resonator oscillator, isolator, PIN modulator, attenuator is fixedly connected sequentially into a structure, one end of described attenuator connects one end that a waveguide turns coaxial converter, the other end that this waveguide turns coaxial converter connects described microstrip antenna, described answer signal coding circuit is fixedly connected on the top of described structure by a support member, the bottom of described structure is provided with a fixed support, this fixed support is fixed in described marine navigation radar servo unit, described marine navigation radar system comprises navar servo unit, radar antenna, waveguide, radar terminal processes and displays equipment.
2. helicopter-guiding system self-checking coded transmitter according to claim 1, it is characterized in that, described answer signal coding circuit is fixedly connected on the top of described dielectric resonator oscillator by a support member.
3. helicopter-guiding system self-checking coded transmitter according to claim 1, it is characterized in that, the bottom of described attenuator, dielectric resonator oscillator is respectively equipped with described fixed support.
4. helicopter-guiding system self-checking coded transmitter according to claim 1, it is characterized in that, an isolator is provided with between described dielectric resonator oscillator and described PIN modulator, for isolating the impact of described PIN modulator sending-end impedance change on described dielectric resonator oscillator, guarantee that dielectric resonator oscillator output frequency is stablized.
5. helicopter-guiding system self-checking coded transmitter according to claim 1, it is characterized in that, described dielectric resonator oscillator uses field effect transistor as active device, described PIN modulator is combined by two PIN switching diodes and waveguide, and described answer signal coding circuit produces the pulse code signal controlling described PIN modulator.
6. helicopter-guiding system self-checking coded transmitter according to claim 1, is characterized in that, described microstrip antenna is by radiation element, dielectric layer and form with reference to ground three parts, and described microstrip antenna adopts coaxial feeding mode.
7. helicopter-guiding system self-checking coded transmitter according to claim 1, it is characterized in that, described marine navigation radar servo unit comprises a marine radar gear case, this marine radar gear case is built-in with a motor, described radar antenna is arranged at above described marine radar gear case, and described motor is for driving described radar antenna.
8. helicopter-guiding system self-checking coded transmitter according to claim 7, it is characterized in that, described dielectric resonator oscillator, PIN modulator, attenuator, microstrip antenna and answer signal coding circuit are all arranged in described marine radar gear case, this marine radar gear case is provided with opening, and described microstrip antenna is close to described opening inner side place.
9. helicopter-guiding system self-checking coded transmitter according to claim 1, it is characterized in that, described dielectric resonator oscillator produces radiofrequency signal, answer signal coding circuit detects radar bow simultaneously, after orientation and trigger pip, the pulse code signal of certain time-delay is produced at particular orientation place, this pulse code signal is sent to described PIN modulator, and then control described PIN modulator radio frequency signal and carry out switch modulation, with the radio-frequency pulse of coded message after modulation, decay through described attenuator, finally by described microstrip antenna to external radiation, normally show on radar terminal processes and displays equipment if the radio-frequency pulse after decay receives after process through radar antenna, then prove that helicopter-guiding system works is normal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420807060.XU CN204422747U (en) | 2014-12-17 | 2014-12-17 | Helicopter-guiding system self-checking coded transmitter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420807060.XU CN204422747U (en) | 2014-12-17 | 2014-12-17 | Helicopter-guiding system self-checking coded transmitter |
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| CN204422747U true CN204422747U (en) | 2015-06-24 |
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| CN201420807060.XU Withdrawn - After Issue CN204422747U (en) | 2014-12-17 | 2014-12-17 | Helicopter-guiding system self-checking coded transmitter |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104502897A (en) * | 2014-12-17 | 2015-04-08 | 上海广电通信技术有限公司 | Self-test code emitter for helicopter pilot system |
| CN117420756A (en) * | 2023-10-16 | 2024-01-19 | 扬州宇安电子科技有限公司 | Airborne radar reconnaissance digital system based on sweep frequency control and automatic attenuation logic |
-
2014
- 2014-12-17 CN CN201420807060.XU patent/CN204422747U/en not_active Withdrawn - After Issue
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104502897A (en) * | 2014-12-17 | 2015-04-08 | 上海广电通信技术有限公司 | Self-test code emitter for helicopter pilot system |
| CN104502897B (en) * | 2014-12-17 | 2017-04-12 | 上海广电通信技术有限公司 | Self-test code emitter for helicopter pilot system |
| CN117420756A (en) * | 2023-10-16 | 2024-01-19 | 扬州宇安电子科技有限公司 | Airborne radar reconnaissance digital system based on sweep frequency control and automatic attenuation logic |
| CN117420756B (en) * | 2023-10-16 | 2024-05-14 | 扬州宇安电子科技股份有限公司 | Airborne radar reconnaissance digital system based on sweep frequency control and automatic attenuation logic |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20150624 Effective date of abandoning: 20170412 |