CN213986844U - Satellite navigation signal amplifier - Google Patents
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- CN213986844U CN213986844U CN202022926154.7U CN202022926154U CN213986844U CN 213986844 U CN213986844 U CN 213986844U CN 202022926154 U CN202022926154 U CN 202022926154U CN 213986844 U CN213986844 U CN 213986844U
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Abstract
The utility model provides a satellite navigation signal amplifier for testing satellite navigation equipment in an equipment cabin, which comprises a display control unit, a signal amplification unit, a power supply unit, a 60-meter cable and a 30-meter cable; the utility model realizes the portable random test of the equipment in the equipment cabin, and solves the difficulty that the discrete amplification equipment can not test the equipment in the equipment cabin rapidly; the filter with the ultralow ripple coefficient is designed to realize the control of the stability of the Beidou system signal, and the problem that the requirement on high flat signals of equipment cabin guidance equipment is high is solved; by introducing a digital detection technology, the amplification signal is detected and controlled in real time, the monitoring requirements of maintenance control personnel are met, and the difficulty that the traditional discrete amplification equipment cannot be monitored in real time due to large size is solved.
Description
Technical Field
The utility model belongs to the technical field of signal test hardware, concretely relates to a signal amplification device for satellite navigation receiver test.
Background
Modern airplanes, rockets and ships are equipped with various navigation devices, and the precision devices are mostly hermetically installed in various device cabins because of high requirements on the use environment and are connected with the outside through various interfaces. The equipment and the equipment cabin need to be disassembled and assembled during testing equipment, because equipment manufacturers are numerous, the fixed connection modes of the equipment and the equipment cabin are also many, the standards are different, the process of installing some equipment to the equipment cabin is complicated, and frequent testing and assembling and disassembling easily cause damage to the equipment or the equipment cabin, so that at present, people do not disassemble the equipment but take out the equipment cabin under many conditions, the equipment is placed in the equipment cabin, the equipment in the equipment cabin is directly tested through an interface of the equipment cabin, and because the equipment cabin on an airplane or a rocket is generally produced and installed by an airplane or a rocket manufacturer together, the disassembling method is very reliable. However, the test method has some problems, such as only being capable of testing equipment cabins which are convenient to move or light in weight, for example, various small equipment cabins at the lower part of an airplane, and the equipment cabin which is the whole rocket shell or the equipment cabin on the ship mast is very inconvenient to test and even difficult to complete.
At present, the satellite navigation receiver adopts an input simulation satellite navigation signal as excitation, and then judges a test result. The satellite signal simulator has low power, a simulated satellite navigation signal needs to be led into tested equipment through a long cable in a special occasion, at the moment, the test requirement can be met only by amplifying an original signal, the existing satellite navigation signal amplifiers are few, and the common power amplifier is difficult to meet the requirements of low noise, high in-band flatness and high out-of-band rejection.
SUMMERY OF THE UTILITY MODEL
In order to overcome the defects of the prior art, the utility model provides a satellite navigation signal amplifier can be used for equipment testing in an equipment cabin, which comprises a display control unit, a signal amplification unit, a power supply unit, a 60-meter cable and a 30-meter cable, wherein the display control unit, the signal amplification unit and the power supply unit are positioned in the satellite navigation signal amplifier, and the display control unit controls the output power of the signal amplification unit; the power supply unit provides other unit working voltages; the test equipment is connected with a satellite navigation signal amplifier through a 60-meter cable, and the satellite navigation signal amplifier is connected with the equipment cabin through a 30-meter cable.
Further, the display control unit receives the detection output signal from the signal amplification unit, calculates and displays the output signal power of the unit after AD sampling; the display control unit controls the amplification coefficient of the signal amplification unit through an attenuation knob on a satellite navigation amplifier panel; the signal amplification unit receives an external analog satellite navigation signal through a 60-meter cable, amplifies the input satellite navigation signal under the control of the display control unit, outputs the amplified signal in two paths, and outputs the amplified signal to a satellite navigation receiver in the equipment cabin through two 30-meter cables; the power supply unit provides voltage required by the operation of other units, and the input of the power supply unit is alternating current 220V or direct current 28V.
Furthermore, the display control unit comprises a CPU module, a panel knob module and a display module, wherein the CPU module inputs a detection output signal of the signal amplification unit, the CPU module outputs an attenuation control signal and an attenuation control signal to the signal amplification unit, the CPU module outputs a display result to the display module, the panel knob module inputs a selection code to the CPU module, and the power supply unit provides a working voltage for the CPU module.
Furthermore, the panel knob module in the display control unit comprises a1 st encoder, a 2 nd encoder, a1 st attenuation knob and a 2 nd attenuation knob; the display module comprises an LED dot matrix and a current digital display meter; the attenuation knob is fixed on the shaft sleeve of the encoder, and when the attenuation knob is rotated, the coding value of the encoder correspondingly changes; the current digital display meter inputs the +5V direct current output by the power supply unit, and the output is connected with the power supply input end of the signal amplification unit; the encoders all adopt 4-bit encoders, and the output of the encoders is binary encoding 0000-1111 states in total; the 1 st attenuation knob and the 1 st encoder output an attenuation code 1 to the CPU module to form a1 st path signal attenuation control code of the signal amplification unit; the 2 nd attenuation knob and the 2 nd encoder output an attenuation code 2 to the CPU module to form a 2 nd signal attenuation control code of the signal amplification unit; the CPU module outputs power data to the LED dot matrix by the signal amplifying unit; the CPU module outputs an attenuation control signal 1 and an attenuation control signal 2 to the signal amplification unit; the current digital display meter displays the power supply current of the signal amplification unit.
Furthermore, the 1 st encoder, the 2 nd encoder, the 1 st attenuation knob and the 2 nd attenuation knob are all NDS 01J; the LED dot matrix adopts LED-054S; the current digital display meter adopts BY 456A; the CPU module adopts STM32F103VET 6; the appearance of the display control unit is of a plug board type structure, and the display control unit is fixed at the middle position of the bottom board of the satellite navigation signal amplifier 1 and has the size: the length is 220mm, the width is 30mm, and the height is 110 mm.
Further, the signal amplification unit comprises a1 st low-noise amplifier, a1 st isolation matching circuit, a 2 nd low-noise amplifier, a 2 nd isolation matching circuit, a cavity duplexer, a 3 rd isolation matching circuit, a1 st RF amplifier, a 4 th isolation matching circuit, a 2 nd RF amplifier, a1 st power divider, a1 st wave detector, a 5 th isolation matching circuit, a 3 rd RF amplifier, a 6 th isolation matching circuit, a 4 th RF amplifier, a 2 nd power divider, a 2 nd wave detector, a power combiner, a1 st numerical control attenuator, a 5 th RF amplifier, a 2 nd numerical control attenuator and a 6 th RF amplifier; the satellite navigation signal is amplified and conditioned by a1 st low-noise amplifier, a1 st isolation matching circuit, a 2 nd low-noise amplifier and a 2 nd isolation matching circuit, and then is sent to a cavity duplexer for preselection filtering and output in two paths, wherein one path of the satellite navigation signal sequentially passes through a 3 rd isolation matching circuit, a1 st RF amplifier, a 4 th isolation matching circuit and a 2 nd RF amplifier and is sent to a1 st power distributor, the other path of the satellite navigation signal sequentially passes through a 5 th isolation matching circuit, a 3 rd RF amplifier, a 6 th isolation matching circuit and a 4 th RF amplifier and is sent to a 2 nd power distributor, the 1 st power distributor divides two paths of signals, one path of the satellite navigation signal is sent to a1 st detector and outputs a detection signal 1 to a display control unit, and the other path of the satellite navigation signal is sent to a power synthesizer; the 2 nd power divider divides two paths of signals, one path of signals is sent to the 2 nd detector to output a detection signal 2 to the display control unit, and the other path of signals is sent to the power synthesizer; the power synthesizer synthesizes the two paths of signals into one path, then distributes the synthesized signal into two paths of signals, one path of signals is output to the 1 st numerical control attenuator, the 1 st numerical control attenuator is output to the 5 th RF amplifier, and the 5 th RF amplifier is output to an interface of a satellite navigation receiver 1 on the equipment cabin through a 30-meter cable; the other path of the signal is output to a 2 nd numerical control attenuator, the 2 nd numerical control attenuator is output to a 6 th RF amplifier, and the 6 th RF amplifier is output to an interface of a satellite navigation receiver 2 on the equipment cabin through a cable with the length of 30 meters; wherein, the input control signal of the 1 st numerical control attenuator is an attenuation control signal 1 output by the display control unit; the 2 nd digital control attenuator inputs the control signal to be the attenuation control signal 2 that the display control unit outputs.
Further, the 1 st low-noise amplifier adopts BLB03, and the 2 nd low-noise amplifier adopts BL 011; the 1 st isolation matching circuit, the 2 nd isolation matching circuit, the 3 rd isolation matching circuit, the 4 th isolation matching circuit, the 5 th isolation matching circuit and the 6 th isolation matching circuit all adopt PAT1220-C-3 DB-T; the cavity duplexer adopts DUP-1260 and 1620; BL011 is adopted for the 1 st RF amplifier, the 2 nd RF amplifier, the 3 rd RF amplifier, the 4 th RF amplifier, the 5 th RF amplifier and the 6 th RF amplifier; the 1 st power divider, the 2 nd power divider and the power combiner all adopt BP2P1 +; the 1 st detector and the 2 nd detector both adopt AD 8313; the 1 st numerical control attenuator and the 2 nd numerical control attenuator both adopt HMC 307; the signal amplification unit is of a rectangular structure, is fixed at the front part of the bottom plate of the satellite navigation signal amplifier 1, and has the following dimensions: the length is 220mm, the width is 60mm, and the height is 110 mm.
Further, the power supply unit comprises an alternating current-direct current conversion module, a1 st direct current transformation module and a 2 nd direct current transformation module, wherein an external alternating current 220V voltage is added to an input end of the alternating current-direct current conversion module, the alternating current-direct current conversion module outputs 28.5V direct current to the 1 st direct current transformation module and the 2 nd direct current transformation module, the 1 st direct current transformation module outputs 5V direct current to the display control unit and the signal amplification unit, and the 2 nd direct current transformation module outputs 3.3V direct current to the display control unit.
Furthermore, the alternating current-direct current conversion module adopts NTA100-220S28-N, the 1 st direct current transformation module adopts HZD30D-24S05, and the 2 nd direct current transformation module adopts LM 1117-3.3.
Further, the satellite navigation signal amplifier appearance is box structure, has the handle on the shell, and the shell material is ABS, and the size is: 300mm long, 150mm wide, 150mm high, the weight is 20 kg.
The utility model realizes the portable random test of the equipment in the equipment cabin, and solves the difficulty that the discrete amplification equipment can not test the equipment in the equipment cabin rapidly; the filter with the ultralow ripple coefficient is designed to realize the control of the stability of the Beidou system signal, and the problem that the requirement on high flat signals of equipment cabin guidance equipment is high is solved; by introducing a digital detection technology, the amplification signal is detected and controlled in real time, the monitoring requirements of maintenance control personnel are met, and the difficulty that the traditional discrete amplification equipment cannot be monitored in real time due to large size is solved.
Drawings
FIG. 1 is a schematic view of the working principle of the present invention;
FIG. 2 is a view of the structure of the present invention;
FIG. 3 is a perspective view of the present invention;
FIG. 4 is a schematic diagram of the operation of the display control unit of the present invention;
FIG. 5 is a block diagram of the display control unit of the present invention;
FIG. 6 is a structural diagram of the signal amplification unit of the present invention;
fig. 7 is a structural diagram of the power supply unit of the present invention.
Description of reference numerals: 1. a satellite navigation signal amplifier; 2. testing equipment; 3. an equipment compartment; 11. a display control unit; 12. A signal amplification unit; 13. a power supply unit; 14. 60 meters of cable; 15. 30 meters of cable; 111. a CPU module; 112. a panel knob module; 113. a display module; 1121. 1, a coder; 1122. a 2 nd encoder; 1123. 1 st attenuation knob; 1124. a 2 nd attenuation knob; 1131. an LED dot matrix; 1132. a current digital display meter; 1201. 1, low noise amplification; 1202. 1 st isolation matching circuit; 1203. 2, low noise amplification; 1204. 2 nd isolation matching circuit; 1205. a cavity duplexer; 1206. a 3 rd isolation matching circuit; 1207. a1 st RF amplifier; 1208. a 4 th isolation matching circuit; 1209. a 2 nd RF amplifier; 1210. 1 st power divider; 1211. a1 st detector; 1212. 5 th isolation matching circuit; 1213. a 3 rd RF amplifier; 1214. a 6 th isolation matching circuit; 1215. a 4 th RF amplifier; 1216. a 2 nd power divider; 1218. a power combiner; 1219. 1 st digital control attenuator; 1220. a 5 th RF amplifier; 1221. a 2 nd numerical control attenuator; 1222. a 6 th RF amplifier; 1301. an AC-DC conversion module; 1302. the 1 st direct current voltage transformation module; 1303. and the 2 nd direct current transformation module.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the following is a detailed description of the present invention with reference to the accompanying drawings and embodiments.
As shown in fig. 1, the utility model discloses a main operating principle is to place satellite navigation signal amplifier between test equipment and equipment cabin, and the measurement input signal of measuring equipment output to satellite navigation signal amplifier is received through the examination equipment that awaits measuring in satellite navigation signal amplifier adjustment, the enlargies back input device cabin, and then obtains the test result.
As shown in fig. 2, in one embodiment of the present invention, the device to be tested is 2 satellite navigation receivers, and the satellite navigation signal amplifier 1 is composed of a display control unit 11, a signal amplification unit 12, a power supply unit 13, a 60-meter cable 14 and a 30-meter cable 15; the display control unit 11, the signal amplification unit 12 and the power supply unit 13 are located inside the satellite navigation signal amplifier 1, the test equipment 2 is connected with the satellite navigation signal amplifier 1 through a 60-meter cable 14, and the satellite navigation signal amplifier 1 is connected with the equipment cabin through a 30-meter cable 15.
The display control unit 11 receives the detection output signal from the signal amplification unit 12, calculates and displays the output signal power of the unit after AD sampling; the display control unit 11 controls the amplification factor of the signal amplification unit 12 through an attenuation knob on the panel of the satellite navigation amplifier 1.
The signal amplification unit 12 receives an external analog satellite navigation signal through a 60-meter cable 14, amplifies the input satellite navigation signal under the control of the display control unit 11, outputs the amplified signal in two paths, and outputs the amplified signal to a satellite navigation receiver in the equipment compartment 3 through a 30-meter cable 15.
The power supply unit 13 supplies voltage required for the operation of other units, and the input of the power supply unit is alternating current 220V or direct current 28V.
As shown in fig. 3, the satellite navigation signal amplifier 1 has a box-shaped structure, a handle is provided on a housing, the housing is made of ABS, and the dimensions are as follows: 300mm long, 150mm wide and 150mm high, and the weight is 20 kg.
As shown in fig. 4, the display control unit 11 includes a CPU module 111, a panel knob module 112, and a display module 113, the CPU module 111 inputs a detection output signal of the signal amplification unit 12, the CPU module 111 outputs an attenuation control signal 1 and an attenuation control signal 2 to the signal amplification unit 12, the CPU module 111 outputs a display result to the display module 113, the panel knob module 112 inputs a selection code to the CPU module 111, and the power supply unit 15 supplies an operating voltage to the CPU module 111.
As shown in fig. 5, the panel knob module 112 in the display control unit 11 includes a1 st encoder 1121, a 2 nd encoder 1122, a1 st attenuation knob 1123, a 2 nd attenuation knob 1124; the display module 113 comprises an LED dot matrix 1131 and a current digital display meter 1132; the attenuation knob is fixed on the shaft sleeve of the encoder, and when the attenuation knob is rotated, the encoding value of the encoder correspondingly changes. The current digital display meter 1132 inputs the +5V direct current output by the power supply unit 13, and outputs the direct current to be connected with the power supply input end of the signal amplification unit 12; the encoders all adopt 4-bit encoders, and the output of the encoders is binary encoding 0000-1111 states in total; the 1 st attenuation knob 1123 and the 1 st encoder 1121 output an attenuation code 1 to the CPU module 111 to form a1 st path signal attenuation control code of the signal amplification unit 12; the 2 nd attenuation knob 1124 and the 2 nd encoder 1122 output an attenuation code 2 to the CPU module 111 to form a 2 nd path signal attenuation control code of the signal amplification unit 12; the CPU module 111 outputs the power data output by the signal amplifying unit 12 to the LED lattice 1131; the CPU module 111 outputs an attenuation control signal 1 and an attenuation control signal 2 to the signal amplification unit 12; the current digital display meter 1132 displays the supply current of the signal amplifying unit 12.
In one embodiment of the present invention, the 1 st encoder 1121, the 2 nd encoder 1122, the 1 st attenuation knob 1123, and the 2 nd attenuation knob 1124 are each an NDS 01J; the LED lattice 1131 adopts LED-054S; the digital current meter 1132 adopts BY 456A; the CPU module 111 employs STM32F103VET 6.
The appearance of the display control unit 11 is a plug board type structure, and is fixed at the middle position of the bottom board of the satellite navigation signal amplifier 1, and the size is as follows: the length is 220mm, the width is 30mm, and the height is 110 mm.
As shown in fig. 6, the signal amplifying unit 12 includes a1 st low noise amplifier 1201, a1 st isolation matching circuit 1202, a 2 nd low noise amplifier 1203, a 2 nd isolation matching circuit 1204, a cavity duplexer 1205, a 3 rd isolation matching circuit 1206, a1 st RF amplifier 1207, a 4 th isolation matching circuit 1208, a 2 nd RF amplifier 1209, a1 st power divider 1210, a1 st detector 1211, a 5 th isolation matching circuit 1212, a 3 rd RF amplifier 1213, a 6 th isolation matching circuit 1214, a 4 th RF amplifier 1215, a 2 nd power divider 1216, a 2 nd detector 1217, a power combiner 1218, a1 st digitally controlled attenuator 1219, a 5 th RF amplifier 1220, a 2 nd digitally controlled attenuator 1221, a 6 th RF amplifier 1222.
The satellite navigation signal is amplified and conditioned by a1 st low noise amplifier 1201, a1 st isolation matching circuit 1202, a 2 nd low noise amplifier 1203, a 2 nd isolation matching circuit 1204, and then sent to a cavity duplexer 1205 for pre-selection filtering and output in two paths, one path of the satellite navigation signal is sent to a1 st power distributor 1210 through a 3 rd isolation matching circuit 1206, a1 st RF amplifier 1207, a 4 th isolation matching circuit 1208, and a 2 nd RF amplifier 1209 in sequence, the other path of the satellite navigation signal is sent to a 2 nd power distributor 1216 through a 5 th isolation matching circuit 1212, a 3 rd RF amplifier 1213, a 6 th isolation matching circuit 1214 and a 4 th RF amplifier 1215 in sequence, the 1 st power distributor 1210 is divided into two paths of signals, one path of the satellite navigation signal is sent to a1 st wave detector 1211 to output a wave detection signal 1 to a display control unit 11, and the other path of the satellite navigation signal is sent to a power synthesizer 1218; the 2 nd power divider 1216 divides two paths of signals, one path is sent to the 2 nd detector 1217 to output a detection signal 2 to the display control unit 11, and the other path is sent to the power combiner 1218; the power combiner 1218 combines the two signals into one path, and then distributes the combined signal into two paths of signals, one path of which is output to the 1 st numerical control attenuator 1219, the 1 st numerical control attenuator 1219 is output to the 5 th RF amplifier 1220, and the 5 th RF amplifier 1220 is output to an interface of the satellite navigation receiver 1 on the equipment cabin through a 30m cable 15; the other path is output to a 2 nd numerically controlled attenuator 1221, the 2 nd numerically controlled attenuator 1221 is output to a 6 th RF amplifier 1222, and the 6 th RF amplifier 1222 is output to an interface of the on-board satellite navigation receiver 2 through a 30-meter cable 15; wherein, the input control signal of the 1 st numerical control attenuator 1219 is the attenuation control signal 1 output by the display control unit 11; the 2 nd digitally controlled attenuator 1221 inputs the control signal as the attenuation control signal 2 outputted from the display control unit 11.
In a specific embodiment of the present invention, the 1 st low noise amplifier 1201 uses BLB03, the 2 nd low noise amplifier 1203 uses BL011, and the noise figure is only 0.38dB using the above ultra-low noise amplifier; PAT1220-C-3DB-T is adopted by the 1 st isolation matching circuit 1202, the 2 nd isolation matching circuit 1204, the 3 rd isolation matching circuit 1206, the 4 th isolation matching circuit 1208, the 5 th isolation matching circuit 1212 and the 6 th isolation matching circuit 1214, the stability control of the Beidou signals is realized by designing a filter with an ultra-low ripple coefficient, the problem of high flat signals of satellite navigation equipment in an equipment compartment is solved, and the actually measured ripple coefficient is less than +/-0.2 dB; the cavity duplexer 1205 adopts DUP-1260-1620, so that the in-band flatness is high, the actually-measured in-band flatness is less than +/-0.1 dB, and meanwhile, the out-of-band rejection is high, and the actually-measured out-of-band rejection is more than 70 dB; the 1 st, 2 nd, 3 rd, 4 th, 5 th, 1220, 6 th RF amplifiers 1207, 1209, 1213, 1215 are all BL 011; the 1 st power divider 1210, the 2 nd power divider 1216 and the power combiner 1218 all adopt BP2P1 +; the 1 st detector 1211 and the 2 nd detector 1217 both adopt AD 8313; the 1 st numerical control attenuator 1219 and the 2 nd numerical control attenuator 1221 both adopt HMC 307.
The signal amplification unit 12 is rectangular in shape, fixed at the front position of the bottom plate of the satellite navigation signal amplifier 1, and has the dimensions: the length is 220mm, the width is 60mm, and the height is 110 mm.
As shown in fig. 6, the power supply unit 13 includes an ac/dc conversion module 1301, a1 st dc transformation module 1302, and a 2 nd dc transformation module 1303, wherein an external ac 220V voltage is applied to an input terminal of the ac/dc conversion module 1301, the ac/dc conversion module 1301 outputs 28.5V dc to the 1 st dc transformation module 1302 and the 2 nd dc transformation module 1303, the 1 st dc transformation module 1302 outputs 5V dc to the display control unit 11 and the signal amplification unit 12, and the 2 nd dc transformation module 1303 outputs 3.3V dc to the display control unit 11.
When the ac 220V is not input, the externally input dc 28.5V voltage can be input to the 1 st dc transformer module 1302 and the 2 nd dc transformer module 1303 via the power interface to generate the operating voltage.
In an embodiment of the present invention, NTA100-220S28-N is used for the AC/DC conversion module 1301, HZD30D-24S05 is used for the 1 st DC transformation module 1302, and LM1117-3.3 is used for the 2 nd DC transformation module 1303.
The power supply unit 13 is rectangular in shape, fixed at the rear position of the bottom plate of the satellite navigation signal amplifier 1, and has the following dimensions: the length is 180mm, the width is 100mm, and the height is 105 mm.
In another embodiment of the present invention, an external satellite navigation signal passes through the left sidewall of the satellite navigation signal amplifier 1 through a 60m radio frequency cable to be connected with the signal amplification unit 12, passes through the right sidewall of the satellite navigation signal amplifier 1 through two 30m radio frequency cables after signal adjustment, amplification and filtering change to be connected with an interface of a shielding darkroom wall, the interface of the shielding darkroom wall is further connected with an aircraft onboard satellite navigation receiver, and a measurement device detects whether parameters of the satellite navigation receiver are normal outside the shielding darkroom.
The utility model realizes the portable random test of the equipment in the equipment cabin by the linear amplification and detection functions of the satellite navigation equipment in the integrated equipment cabin, and solves the difficulty that the discrete amplification equipment can not test the equipment in the equipment cabin rapidly; the filter with the ultralow ripple coefficient is designed to realize the control of the stability of the Beidou system signal, and the problem that the requirement on high flat signals of equipment cabin guidance equipment is high is solved; by introducing a digital detection technology, the amplification signal is detected and controlled in real time, the monitoring requirements of maintenance control personnel are met, and the difficulty that the traditional discrete amplification equipment cannot be monitored in real time due to large size is solved.
Claims (10)
1. A satellite navigation signal amplifier comprises a display control unit (11), a signal amplification unit (12), a power supply unit (13), a 60-meter cable (14) and a 30-meter cable (15), and is characterized in that: the display control unit (11), the signal amplification unit (12) and the power supply unit (13) are positioned in the satellite navigation signal amplifier (1), and the display control unit (11) controls the output power of the signal amplification unit (12); the power supply unit (13) provides other unit working voltages; the testing equipment (2) is connected with the satellite navigation signal amplifier (1) through a 60-meter cable (14), and the satellite navigation signal amplifier (1) is connected with the equipment cabin through a 30-meter cable (15).
2. A satellite navigation signal amplifier as claimed in claim 1, wherein: the display control unit (11) receives the detection output signal from the signal amplification unit (12), calculates and displays the output signal power of the unit after AD sampling; the display control unit (11) controls the amplification factor of the signal amplification unit (12) through an attenuation knob on a panel of the satellite navigation signal amplifier (1); the signal amplification unit (12) receives an external simulated satellite navigation signal through a 60-meter cable (14), amplifies the input satellite navigation signal under the control of the display control unit (11), outputs the amplified signal in two paths, and outputs the amplified signal to a satellite navigation receiver in the equipment cabin (3) through two 30-meter cables (15); the power supply unit (13) provides voltage required by the operation of other units, and the input of the power supply unit is alternating current 220V or direct current 28V.
3. A satellite navigation signal amplifier as claimed in claim 2, wherein: the display control unit (11) comprises a CPU module (111), a panel knob module (112) and a display module (113), wherein the CPU module (111) inputs a detection output signal of the signal amplification unit (12), the CPU module (111) outputs an attenuation control signal 1 and an attenuation control signal 2 to the signal amplification unit (12), the CPU module (111) outputs a display result to the display module (113), the panel knob module (112) inputs a selection code to the CPU module (111), and the power supply unit (13) provides working voltage for the CPU module (111).
4. A satellite navigation signal amplifier as claimed in claim 3, wherein: the panel knob module (112) in the display control unit (11) comprises a1 st encoder (1121), a 2 nd encoder (1122), a1 st attenuation knob (1123) and a 2 nd attenuation knob (1124); the display module (113) comprises an LED dot matrix (1131) and a current digital display meter (1132); the attenuation knob is fixed on the shaft sleeve of the encoder, and when the attenuation knob is rotated, the coding value of the encoder correspondingly changes; the current digital display meter (1132) inputs the +5V direct current output by the power supply unit (13), and the output is connected with the power supply input end of the signal amplification unit (12); the encoders all adopt 4-bit encoders, and the output of the encoders is binary encoding 0000-1111 states in total; the 1 st attenuation knob (1123) and the 1 st encoder (1121) output an attenuation code 1 to the CPU module (111) to form a1 st path signal attenuation control code of the signal amplification unit (12); the 2 nd attenuation knob (1124) and the 2 nd encoder (1122) output attenuation codes 2 to the CPU module (111) to form a 2 nd signal attenuation control code of the signal amplification unit (12); the CPU module (111) outputs power data to the LED dot matrix (1131) by the signal amplifying unit (12); the CPU module (111) outputs an attenuation control signal 1 and an attenuation control signal 2 to the signal amplification unit (12); the current digital display meter (1132) displays the power supply current of the signal amplification unit (12).
5. The satellite navigation signal amplifier of claim 4, wherein: the 1 st encoder (1121), the 2 nd encoder (1122), the 1 st attenuation knob (1123) and the 2 nd attenuation knob (1124) adopt NDS 01J; the LED dot matrix (1131) adopts LED-054S; the digital current indicator (1132) adopts BY 456A; the CPU module (111) adopts STM32F103VET 6; the appearance of the display control unit (11) is of a plug board type structure, and the display control unit is fixed at the middle position of a bottom plate of the satellite navigation signal amplifier (1) and has the size: the length is 220mm, the width is 30mm, and the height is 110 mm.
6. A satellite navigation signal amplifier as claimed in claim 2, wherein: the signal amplification unit (12) comprises a1 st low-noise amplifier (1201), a1 st isolation matching circuit (1202), a 2 nd low-noise amplifier (1203), a 2 nd isolation matching circuit (1204), a cavity duplexer (1205), a 3 rd isolation matching circuit (1206), a1 st RF amplifier (1207), a 4 th isolation matching circuit (1208), a 2 nd RF amplifier (1209), a1 st power divider (1210), a1 st detector (1211), a 5 th isolation matching circuit (1212), a 3 rd RF amplifier (1213), a 6 th isolation matching circuit (1214), a 4 th RF amplifier (1215), a 2 nd power divider (1222), a 2 nd detector (1217), a power combiner (1218), a1 st numerical control attenuator (1219), a 5 th RF amplifier (1220), a 2 nd numerical control attenuator (1221) and a 6 th RF amplifier (1216); wherein, after the satellite navigation signal is amplified and conditioned by a1 st low noise amplifier (1201), a1 st isolation matching circuit (1202), a 2 nd low noise amplifier (1203) and a 2 nd isolation matching circuit (1204), sending the signal into a cavity duplexer (1205) for preselection filtering and outputting the signal in two paths, wherein one path sequentially passes through a 3 rd isolation matching circuit (1206), a1 st RF amplifier (1207), a 4 th isolation matching circuit (1208) and a 2 nd RF amplifier (1209) and is sent to a1 st power distributor (1210), the other path sequentially passes through a 5 th isolation matching circuit (1212), a 3 rd RF amplifier (1213), a 6 th isolation matching circuit (1214) and a 4 th RF amplifier (1215) and is sent to a 2 nd power distributor (1216), the 1 st power distributor (1210) divides two paths of signals, one path is sent to a1 st detector (1211) and outputs a detection signal 1 to a display control unit (11), and the other path is sent to a power combiner (1218); the 2 nd power divider (1216) divides two paths of signals, one path of signals is sent to the 2 nd detector (1217) to output one path of detection signals 2 to the display control unit (11), and the other path of signals is sent to the power combiner (1218); the power combiner (1218) combines the two paths of signals into one path, then distributes the combined signal into two paths of signals, one path of signals is output to the 1 st numerical control attenuator (1219), the 1 st numerical control attenuator (1219) is output to the 5 th RF amplifier (1220), and the 5 th RF amplifier (1220) is output to an interface of the satellite navigation receiver 1 on the equipment cabin through a 30-meter cable (15); the other path is output to a 2 nd numerically controlled attenuator (1221), the 2 nd numerically controlled attenuator (1221) is output to a 6 th RF amplifier (1222), and the 6 th RF amplifier (1222) is output to an interface of the on-board satellite navigation receiver 2 through a cable (15) of 30 meters; wherein, the input control signal of the 1 st numerical control attenuator (1219) is the attenuation control signal 1 output by the display control unit (11); the 2 nd numerical control attenuator (1221) inputs a control signal which is the attenuation control signal 2 output by the display control unit (11).
7. A satellite navigation signal amplifier as claimed in claim 6, wherein: the 1 st low noise amplifier (1201) adopts BLB03, and the 2 nd low noise amplifier (1203) adopts BL 011; PAT1220-C-3DB-T is adopted by a1 st isolation matching circuit (1202), a 2 nd isolation matching circuit (1204), a 3 rd isolation matching circuit (1206), a 4 th isolation matching circuit (1208), a 5 th isolation matching circuit (1212) and a 6 th isolation matching circuit (1214); the cavity duplexer (1205) adopts DUP-1260 and 1620; BL011 is adopted for the 1 st RF amplifier (1207), the 2 nd RF amplifier (1209), the 3 rd RF amplifier (1213), the 4 th RF amplifier (1215), the 5 th RF amplifier (1220) and the 6 th RF amplifier (1222); the 1 st power divider (1210), the 2 nd power divider (1216) and the power combiner (1218) all adopt BP2P1 +; the 1 st wave detector (1211) and the 2 nd wave detector (1217) both adopt AD 8313; the 1 st numerical control attenuator (1219) and the 2 nd numerical control attenuator (1221) both adopt HMC 307; the signal amplification unit (12) is of a rectangular structure, is fixed at the front part of the bottom plate of the satellite navigation signal amplifier (1), and has the following dimensions: the length is 220mm, the width is 60mm, and the height is 110 mm.
8. A satellite navigation signal amplifier as claimed in claim 2, wherein: the power supply unit (13) comprises an alternating current-direct current conversion module (1301), a1 st direct current transformation module (1302) and a 2 nd direct current transformation module (1303), wherein an external alternating current 220V voltage is added to an input end of the alternating current-direct current conversion module (1301), the alternating current-direct current conversion module (1301) outputs 28.5V direct current to the 1 st direct current transformation module (1302) and the 2 nd direct current transformation module (1303), the 1 st direct current transformation module (1302) outputs 5V direct current to the display control unit (11), the signal amplification unit (12), and the 2 nd direct current transformation module (1303) outputs 3.3V direct current to the display control unit (11).
9. A satellite navigation signal amplifier as claimed in claim 8, wherein: the alternating current-direct current conversion module (1301) adopts NTA100-220S28-N, the 1 st direct current transformation module (1302) adopts HZD30D-24S05, and the 2 nd direct current transformation module (1303) adopts LM 1117-3.3.
10. A satellite navigation signal amplifier as claimed in claim 2, wherein: the appearance of the satellite navigation signal amplifier (1) is of a box-type structure, a handle is arranged on a shell, the shell is made of ABS (acrylonitrile butadiene styrene), and the size is as follows: 300mm long, 150mm wide, 150mm high, the weight is 20 kg.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022926154.7U CN213986844U (en) | 2020-12-09 | 2020-12-09 | Satellite navigation signal amplifier |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022926154.7U CN213986844U (en) | 2020-12-09 | 2020-12-09 | Satellite navigation signal amplifier |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213986844U true CN213986844U (en) | 2021-08-17 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022926154.7U Expired - Fee Related CN213986844U (en) | 2020-12-09 | 2020-12-09 | Satellite navigation signal amplifier |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213986844U (en) |
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2020
- 2020-12-09 CN CN202022926154.7U patent/CN213986844U/en not_active Expired - Fee Related
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Granted publication date: 20210817 Termination date: 20211209 |