CN110823019B - Testing device and testing method for airborne transmitting Beidou satellite signals - Google Patents
Testing device and testing method for airborne transmitting Beidou satellite signals Download PDFInfo
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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Abstract
A testing device for airborne transmitting Beidou satellite signals comprises an airborne transmitting Beidou signal device, an airborne transmitting Beidou signal power testing device, an airborne transmitting Beidou signal link time delay testing device and an missile-borne Beidou signal processing module adaptability testing device; the power of the Beidou signal transmitted to the missile-borne Beidou signal processing module by the Beidou signal transmitting power testing device of the loader is measured; the time delay test device for the Beidou signal link transmitted by the loader is used for measuring the time delay of the Beidou signal transmitted to the missile-borne Beidou signal processing module by the loader; the method comprises the following steps that through a missile-borne Beidou signal processing module adaptability testing device, the switching speed and reliability of a missile-borne positioning receiver and a missile-borne Beidou signal processing module are measured when a missile is separated from a carrier; the test device and the test method for the airborne Beidou satellite signal transmission are displayed by a large amount of mooring and flying and target test data of a certain radar type air-to-air missile, and the test result of the test method is accurate, reliable and effective.
Description
Technical Field
The invention relates to the technical field of research and development testing of air-to-air missiles, in particular to a testing device and a testing method for a carrier to transmit Beidou satellite signals.
Background
The newly developed novel radar air-to-air missile uses the combination of Beidou and inertial navigation as a scheme for guidance of a flying section in the missile. Under normal conditions, the flight time of the air-to-air missile is tens of seconds, and the cold start positioning time of the Beidou satellite missile-borne positioning receiver and the missile-borne Beidou signal processing module is 40-60 seconds; therefore, the missile-borne positioning receiver and the missile-borne Beidou signal processing module need to utilize a carrier to forward a Beidou satellite signal for positioning in advance in a missile flight section, and store priori information such as ephemeris, Doppler and pseudo code phase in the missile-borne positioning receiver and the missile-borne Beidou signal processing module; after the missile is launched, the missile-borne positioning receiver utilizes the stored prior information to realize rapid recapture positioning, the starting switching time of the Beidou satellite missile-borne positioning receiver and the missile-borne Beidou signal processing module is greatly shortened, and the normal work of the combination of Beidou guidance and inertial navigation in the launching process of the missile is ensured.
However, when the missile is in the missile-borne state, the distance between the airborne Beidou antenna and the missile is too long, and when a radio-frequency signal received by the airborne Beidou antenna is transmitted to the missile-borne Beidou signal processing module through a radio-frequency coaxial cable, serious signal attenuation and time delay are generated, if the signal attenuation and time delay exceed the range of design indexes, the missile can possibly fail to accurately obtain and store priori information such as ephemeris, Doppler and pseudo code phases at the missile-borne section, so that the missile-borne positioning receiver can not utilize the stored priori information to realize rapid recapture positioning after the missile is launched, and the precision of guidance at the missile-borne section can be directly influenced.
Because the running time of the second-generation Beidou navigation system in China is short, a novel radar air-to-air missile is the first application of the Beidou satellite positioning technology, and therefore no relevant detection device and method for transmitting Beidou satellite signals by a carrier exists.
Disclosure of Invention
In order to overcome the defects in the background art, the invention discloses a testing device and a testing method for transmitting a Beidou satellite signal by an airborne machine; the testing arrangement that big dipper satellite signal was forwardded to the carrier includes: the system comprises an airborne Beidou signal transmitting device, an airborne Beidou signal transmitting power testing device, an airborne Beidou signal transmitting link time delay testing device and a missile-borne Beidou signal processing module adaptability testing device; the power of the Beidou signal transmitted to the missile-borne Beidou signal processing module by the Beidou signal transmitting power testing device of the loader is measured; the time delay test device for the Beidou signal link transmitted by the loader is used for measuring the time delay of the Beidou signal transmitted to the missile-borne Beidou signal processing module by the loader; by the missile-borne Beidou signal processing module adaptability testing device, the switching speed and reliability of the missile-borne positioning receiver and the missile-borne Beidou signal processing module are tested when the missile is separated from the carrier; the test device and the test method for the airborne Beidou satellite signal transmission are displayed by a large amount of mooring, flying and target test data of a certain radar type air-to-air missile, and the test result of the device and the test method is accurate, reliable and effective.
In order to realize the purpose, the invention adopts the following technical scheme: a testing device for airborne transmitting Beidou satellite signals comprises an airborne transmitting Beidou signal device, an airborne transmitting Beidou signal power testing device, an airborne transmitting Beidou signal link time delay testing device and an missile-borne Beidou signal processing module adaptability testing device; the carrier-borne Beidou satellite signal transmitting device is used for simulating radio frequency signals transmitted to the missile-borne Beidou signal processing module by the carrier; the airborne Beidou signal power test device is used for measuring the power of the airborne Beidou signal transmitted to the missile-borne Beidou signal processing module by the airborne Beidou signal; the airborne Beidou signal transmission link time delay testing device is used for measuring the time delay of the airborne Beidou signal transmission to the missile-borne Beidou signal processing module; the missile-borne Beidou signal processing module adaptability testing device is used for measuring the switching response speed and reliability of the missile-borne positioning receiver and the missile-borne Beidou signal processing module when the missile is separated from the carrier;
the airborne Beidou antenna, the active power distributor, the transmitting frame electrical connecting device and the blocking module are sequentially connected through a radio frequency coaxial cable;
the power testing device for the airborne Beidou signal transmission comprises a low-noise signal amplifier and a frequency spectrograph; the low-noise signal amplifier and the frequency spectrograph are connected through a radio frequency coaxial cable, and the low-noise signal amplifier is connected with the blocking module through the radio frequency coaxial cable;
the load machine transmission Beidou signal link time delay testing device comprises a low noise signal amplifier, time delay testing equipment and a Beidou B3 active antenna; the low-noise signal amplifier and the time delay testing equipment are connected through a radio frequency coaxial cable, and the low-noise signal amplifier and the blocking module are connected through the radio frequency coaxial cable; the time delay test equipment and the Beidou B3 active antenna are connected through a radio frequency coaxial cable;
the missile-borne Beidou signal processing module adaptability testing device comprises a Beidou B3 active antenna, a missile-borne Beidou signal processing module and receiver testing equipment; the missile-borne Beidou signal processing module and the blocking module are connected through a radio frequency coaxial cable; the missile-borne Beidou signal processing module and the Beidou B3 active antenna are connected through a radio frequency coaxial cable; the missile-borne Beidou signal processing module and the receiver testing equipment are connected through a testing cable.
Furthermore, the time delay test equipment comprises two Beidou satellite signal receivers and a two-channel digital oscilloscope; the two Beidou satellite signal receivers are respectively connected with the low noise signal amplifier and the Beidou B3 active antenna through radio frequency coaxial cables, and two channels of the two-channel digital oscilloscope are respectively connected with the two Beidou satellite signal receivers through test cables; the two Beidou satellite signal receivers are used for demodulating Beidou signals transmitted by the aerial carrier and Beidou B3 active antenna signals, Pulse Per Second (PPS) signals of the two signals are respectively separated, and the PPS signals of the two signals are input into the two-channel digital oscilloscope and are used for measuring phases (time differences).
Furthermore, the missile-borne Beidou signal processing module is a part of a novel radar type air-to-air missile Beidou guidance device and is provided with a forwarding signal receiving port and a missile-borne receiver signal receiving port; the transmitting signal receiving port is used for inputting a Beidou signal to the airborne machine through a radio frequency coaxial cable to transmit, and the signal receiving port of the missile-borne receiver is used for inputting a Beidou B3 active antenna signal through the radio frequency coaxial cable; in the adaptability test process of the missile-borne Beidou signal processing module, the Beidou signal needs to be forwarded by an aircraft which is input through a signal receiving port, and the Beidou B3 active antenna signal input through a signal receiving port of a missile-borne receiver is switched.
Furthermore, the receiver test equipment is a computer provided with a test program, and the test program is specially developed for the adaptability test of the Beidou signal processing module.
Based on the testing device that the aerial carrier transmits the Beidou satellite signal, the testing method that the aerial carrier transmits the Beidou satellite signal comprises the following steps: the method comprises three sub-items of a power test of the Beidou signal transmitted by the aerial carrier, a time delay test of a Beidou signal transmitted by the aerial carrier and an adaptability test of a missile-borne Beidou signal processing module.
Further, the specific test method for the power test subentry of the carrier transmitting the Beidou signal is as follows:
s11, forwarding the Beidou signal by the calibration loader to test the insertion loss LdBm of the accessed radio frequency coaxial cable;
s12, setting the amplification gain G dBm of the low-noise signal amplifier;
s13, setting the center frequency point of the frequency spectrograph to be a B3 frequency point and corresponding test bandwidth, wherein the measurement mode is power measurement;
s14, powering on the Beidou antenna and the active power distributor, observing whether the frequency spectrograph is flat in a B3 frequency band after the signals are stable, and recording the frequency characteristics of the frequency spectrograph if abnormal interference signal wave crests exist; recording in-band noise power if no interference exists; repeating the measurement for 3 times, and calculating and solving the noise average power value P0 dBm;
s15, the calculation carrier forwards the Beidou signal power value P, and the calculation formula is as follows: P-P0-G- (-101) + (-130) + L-P0-G + L-29 dBm;
s16, comparing the calculated power value P of the Beidou signal forwarded by the aircraft with the design index, and judging whether the design index is met.
Further, the specific test method of the carrier transmitting Beidou signal link time delay test sub-item is as follows:
s21, setting a Beidou B3 active antenna far away from the test carrier;
s22, setting the amplification gain G dBm of the low-noise signal amplifier;
s23, the carrier transmits the Beidou satellite signals and the Beidou B3 active antenna signals and simultaneously accesses the time delay test equipment;
s24, measuring the phase difference of two paths of Pulse Per Second (PPS) of the Beidou satellite signal and the Beidou B3 active antenna signal transmitted by the carrier, repeatedly measuring for three times, and calculating the average value T of the phase difference, namely the time delay of the Beidou satellite signal transmitted by the carrier;
and S25, comparing the calculated time delay T of the Beidou signal transmission link of the aircraft with the design index, and judging whether the design index is met.
Further, the specific test method for the missile-borne Beidou signal processing module adaptability test sub-item comprises the following steps:
s31, setting a Beidou B3 active antenna far away from the test carrier;
s32, the checking and calibration measurement carrier transmits Beidou satellite signals and Beidou B3 active antenna signals, and the two paths of signals are guaranteed to work normally;
s33, the carrier transmits Beidou satellite signals and Beidou B3 active antenna signals and simultaneously accesses the missile-borne Beidou signal processing module; the Beidou satellite signal is transmitted by the aerial carrier to be accessed into a transmitting signal receiving port, and the Beidou B3 active antenna signal is accessed into a missile-borne receiver signal receiving port;
s34, connecting the missile-borne Beidou signal processing module and the receiver testing equipment through a testing cable;
s35, the airborne Beidou antenna and the active power distributor are electrified and started; the missile-borne Beidou signal processing module is set to be in a hanging flight mode through receiver testing equipment and used for simulating the working condition of the missile-borne Beidou signal processing module in the missile hanging flight mode when the airborne machine forwards the Beidou satellite signal for access;
s36, controlling the missile-borne Beidou signal processing module to be in cold start through receiver testing equipment, and automatically recording the cold start time and the satellite receiving number of the missile-borne Beidou signal processing module, the signal-to-noise ratio of a carrier-transmitted Beidou satellite signal and channel AD power data by the receiver testing equipment; meanwhile, measuring and analyzing the positioning precision, the speed measurement precision, the pseudo range precision and the pseudo range precision by utilizing a receiver testing device;
s37, the missile-borne Beidou signal processing module is set to be in an autonomous flight mode through the receiver testing equipment, the receiver testing equipment automatically records the recapture positioning response time when the missile-borne Beidou signal processing module forwards the Beidou satellite signals from the carrier and switches to the Beidou B3 active antenna signals, and when the test missile is simulated to be separated from the carrier, the Beidou satellite signals are switched to the response speed and the reliability of the missile-borne positioning receiver and the missile-borne Beidou signal processing module.
Due to the adoption of the technical scheme, the invention has the following beneficial effects: the invention discloses a testing device for an airborne machine to transmit Beidou satellite signals, which comprises an airborne machine transmitting Beidou signal device, an airborne machine transmitting Beidou signal power testing device, an airborne machine transmitting Beidou signal link time delay testing device and a missile-borne Beidou signal processing module adaptability testing device, wherein the airborne machine transmitting Beidou signal power testing device is connected with the airborne machine transmitting Beidou signal power testing device; the power of the Beidou signal transmitted to the missile-borne Beidou signal processing module by the Beidou signal transmitting power testing device of the loader is measured; the time delay test device for the Beidou signal link transmitted by the loader is used for measuring the time delay of the Beidou signal transmitted to the missile-borne Beidou signal processing module by the loader; the method comprises the following steps that through a missile-borne Beidou signal processing module adaptability testing device, the switching speed and reliability of a missile-borne positioning receiver and a missile-borne Beidou signal processing module are measured when a missile is separated from a carrier; the test device and the test method for the airborne Beidou satellite signal transmission are verified by a large amount of mooring, hanging and target test data of a certain radar type air-to-air missile, and the test result of the device and the test method is accurate, reliable and effective.
Drawings
Fig. 1 is a schematic diagram of a testing device for transmitting Beidou satellite signals by an aircraft.
In the figure: 1. an airborne Beidou antenna; 2. an active power splitter; 3. a launcher electrical connection; 4. a blocking module; 5. a low noise signal amplifier; 6. a frequency spectrograph; 7. a delay test device; 8. beidou B3 active antenna; 9. the missile-borne Beidou signal processing module; 10. the receiver tests the device.
Detailed Description
The present invention will be explained in detail by the following examples, which are disclosed for the purpose of protecting all technical improvements within the scope of the present invention.
A testing device for airborne transmitting Beidou satellite signals comprises an airborne transmitting Beidou signal device, an airborne transmitting Beidou signal power testing device, an airborne transmitting Beidou signal link time delay testing device and an missile-borne Beidou signal processing module adaptability testing device;
the airborne Beidou satellite signal forwarding device comprises an airborne Beidou antenna 1, an active power distributor 2, a launcher electrical connecting device 3 and a blocking module 4, wherein the airborne Beidou antenna 1, the active power distributor 2, the launcher electrical connecting device 3 and the blocking module 4 are sequentially connected through a radio frequency coaxial cable;
the power testing device for the airborne Beidou signal comprises a low noise signal amplifier 5 and a frequency spectrograph 6; the low-noise signal amplifier 5 and the frequency spectrograph 6 are connected through a radio frequency coaxial cable, and the low-noise signal amplifier 5 and the blocking module 4 are connected through a radio frequency coaxial cable;
the airborne transmitting Beidou signal link time delay testing device comprises a low noise signal amplifier 5, time delay testing equipment 7 and a Beidou B3 active antenna 8; the low-noise signal amplifier 5 and the time delay testing equipment 7 are connected through a radio frequency coaxial cable, and the low-noise signal amplifier 5 and the blocking module 4 are connected through the radio frequency coaxial cable; the time delay test equipment 7 and the Beidou B3 active antenna 8 are connected through a radio frequency coaxial cable; the time delay testing device 7 comprises two Beidou satellite signal receivers and a two-channel digital oscilloscope; the two Beidou satellite signal receivers are respectively connected with the low noise signal amplifier 5 and the Beidou B3 active antenna 8 through radio frequency coaxial cables, and two channels of the two-channel digital oscilloscope are respectively connected with the two Beidou satellite signal receivers through test cables;
the missile-borne Beidou signal processing module adaptability testing device comprises a Beidou B3 active antenna 8, a missile-borne Beidou signal processing module 9 and receiver testing equipment 10; the missile-borne Beidou signal processing module 9 and the blocking module 4 are connected through a radio frequency coaxial cable; the missile-borne Beidou signal processing module 9 and the Beidou B3 active antenna 8 are connected through a radio frequency coaxial cable; the missile-borne Beidou signal processing module 9 and the receiver testing equipment 10 are connected through a testing cable; the missile-borne Beidou signal processing module 9 is provided with a forwarding signal receiving port and a missile-borne receiver signal receiving port, the forwarding signal receiving port is used for inputting a carrier to forward a Beidou signal, the missile-borne receiver signal receiving port is used for inputting a Beidou B3 active antenna 8 signal, and the missile-borne receiver signal receiving port is used for inputting a missile-borne positioning receiver signal when the missile-borne Beidou signal processing module 9 works normally; the receiver test equipment 10 is a computer provided with a test program;
the test method of the test device for the airborne Beidou satellite signal transmission comprises three sub-items, namely an airborne Beidou signal transmission power test, an airborne Beidou signal transmission link time delay test and an missile-borne Beidou signal processing module adaptability test;
the specific test method of the power test subentry of the carrier-borne Beidou signal is as follows:
s11, forwarding the Beidou signal by the calibration loader to test the insertion loss LdBm of the accessed radio frequency coaxial cable;
s12, setting an amplification gain G dBm of the low-noise signal amplifier 5;
s13, setting the center frequency point of the spectrometer 6 as a B3 frequency point 1268.52MHz, setting the bandwidth as 20.16MHz and setting the measurement mode as power measurement;
s14, powering up and starting the Beidou antenna 1 of the carrier and the active power distributor 2, observing whether the frequency spectrograph 6 is flat in a B3 frequency band after signals are stable, and recording the frequency characteristics of the abnormal interference signal if the abnormal interference signal wave crest exists; recording in-band noise power if no interference exists; repeating the measurement for 3 times, and calculating and solving the noise average power value P0 dBm;
s15, the calculation carrier forwards the Beidou signal power value P, and the calculation formula is as follows: P-P0-G- (-101) + (-130) + L-P0-G + L-29 dBm;
s16, comparing the power value P of the Beidou signal forwarded by the aircraft obtained through calculation with a design index, and judging whether the power value P meets the design index;
the specific test method of the sub item of the Beidou signal link time delay test forwarded by the aircraft comprises the following steps:
s21, erecting a Beidou B3 active antenna 8 ten meters away from the test carrier;
s22, setting an amplification gain G dBm of the low-noise signal amplifier 5;
s23, the carrier transmits the Beidou satellite signals and the Beidou B3 active antenna 8 signals and simultaneously accesses the time delay test equipment 7;
s24, measuring the phase difference of two paths of Pulse Per Second (PPS) of the Beidou satellite signal and the Beidou B3 active antenna 8 signal transmitted by the carrier, repeatedly measuring for three times, and calculating the average value T of the phase difference, namely the time delay of the Beidou satellite signal transmitted by the carrier;
and S25, comparing the calculated time delay T of the Beidou signal transmission link of the aircraft with the design index, and judging whether the design index is met.
Further, the specific test method for the missile-borne Beidou signal processing module adaptability test sub-item comprises the following steps:
s31, erecting a Beidou B3 active antenna 8 ten meters away from the test carrier;
s32, the checking and calibration measurement carrier forwards Beidou satellite signals and Beidou B3 active antenna 8 signals, and the two paths of signals are guaranteed to work normally;
s33, the carrier transmits Beidou satellite signals and Beidou B3 active antenna 8 signals and simultaneously accesses the missile-borne Beidou signal processing module 9; the Beidou satellite signal is transmitted by the aerial carrier to be accessed into a transmitting signal receiving port, and the Beidou B3 active antenna 8 signal is accessed into a missile-borne receiver signal receiving port;
s34, connecting the missile-borne Beidou signal processing module 9 and the receiver testing equipment 10 through a testing cable;
s35, the airborne Beidou antenna 1 and the active power distributor 2 are powered on and started; the missile-borne Beidou signal processing module 9 is set to be in a hanging flight mode through the receiver testing equipment 10, and the working condition of the missile-borne Beidou signal processing module 9 in the missile hanging flight mode when the carrier forwards the Beidou satellite signal for access is simulated;
s36, controlling the missile-borne Beidou signal processing module 9 to be in cold start through the receiver testing equipment 10, and automatically recording the cold start time, the satellite receiving number, the signal-to-noise ratio of the missile-borne Beidou signal processing module 9 and the channel AD power data by the receiver testing equipment 10; meanwhile, the receiver test equipment 10 is used for measuring and analyzing the positioning precision, the speed measurement precision, the pseudo range precision and the pseudo range precision;
s37, the missile-borne Beidou signal processing module 9 is set to be in an autonomous flight mode through the receiver testing device 10, the receiver testing device 10 automatically records recapture positioning time when the missile-borne Beidou signal processing module 9 forwards a Beidou satellite signal from an aerial carrier and switches to a Beidou B3 active antenna 8 signal, and when a simulation test missile is separated from the aerial carrier, the Beidou satellite signal is switched to the response speed and reliability of the missile-borne positioning receiver and the missile-borne Beidou signal processing module 9.
The present invention is not described in detail in the prior art.
Claims (5)
1. The utility model provides a testing arrangement of big dipper satellite signal is forwardded to machine carrier which characterized by: the system comprises an airborne Beidou signal transmitting device, an airborne Beidou signal transmitting power testing device, an airborne Beidou signal transmitting link time delay testing device and a missile-borne Beidou signal processing module adaptability testing device;
the airborne Beidou signal forwarding device comprises an airborne Beidou antenna (1), an active power distributor (2), a transmitting rack electrical connecting device (3) and a blocking module (4), wherein the airborne Beidou antenna (1), the active power distributor (2), the transmitting rack electrical connecting device (3) and the blocking module (4) are sequentially connected through a radio frequency coaxial cable;
the power testing device for the airborne Beidou signal comprises a low-noise signal amplifier (5) and a frequency spectrograph (6); the low-noise signal amplifier (5) and the frequency spectrograph (6) are connected through a radio frequency coaxial cable, and the low-noise signal amplifier (5) and the blocking module (4) are connected through a radio frequency coaxial cable;
the airborne transmitting Beidou signal link time delay testing device comprises a low noise signal amplifier (5), time delay testing equipment (7) and a Beidou B3 active antenna (8); the low-noise signal amplifier (5) and the time delay testing equipment (7) are connected through a radio frequency coaxial cable, and the low-noise signal amplifier (5) and the blocking module (4) are connected through the radio frequency coaxial cable; the time delay test equipment (7) and the Beidou B3 active antenna (8) are connected through a radio frequency coaxial cable;
the missile-borne Beidou signal processing module adaptability testing device comprises a Beidou B3 active antenna (8), a missile-borne Beidou signal processing module (9) and receiver testing equipment (10); the missile-borne Beidou signal processing module (9) and the blocking module (4) are connected through a radio frequency coaxial cable; the missile-borne Beidou signal processing module (9) and the Beidou B3 active antenna (8) are connected through a radio frequency coaxial cable; the missile-borne Beidou signal processing module (9) and the receiver testing equipment (10) are connected through a testing cable.
2. The test device for the airborne vehicle to transmit the Beidou satellite signal according to claim 1, wherein: the time delay testing equipment (7) comprises two Beidou satellite signal receivers and a two-channel digital oscilloscope; the two Beidou satellite signal receivers are respectively connected with the low noise signal amplifier (5) and the Beidou B3 active antenna (8) through radio frequency coaxial cables, and the two channels of the two-channel digital oscilloscope are respectively connected with the two Beidou satellite signal receivers through test cables.
3. The test device for the airborne vehicle to transmit the Beidou satellite signal according to claim 1, wherein: the missile-borne Beidou signal processing module (9) is provided with a forwarding signal receiving port and a missile-borne receiver signal receiving port.
4. The test device for the airborne vehicle to transmit the Beidou satellite signal according to claim 1, wherein: the receiver test equipment (10) is a computer provided with a test program.
5. A test method of a test device for transmitting Beidou satellite signals by an airborne machine is characterized by comprising the following steps: the method comprises three sub-test items, namely an airborne Beidou signal transmitting power test, an airborne Beidou signal transmitting link time delay test and an missile-borne Beidou signal processing module adaptability test;
the specific test method for the power test of the Beidou signal transmitted by the aerial carrier is as follows:
s11, forwarding the Beidou signal by the calibration loader to test the insertion loss L dBm of the accessed radio frequency coaxial cable;
s12, setting an amplification gain G dBm of a low-noise signal amplifier (5);
s13, setting the center frequency point of the frequency spectrograph (6) as a B3 frequency point and a corresponding bandwidth, and setting the measurement mode as power measurement;
s14, powering on and starting the airborne Beidou antenna (1) and the active power distributor (2), and observing whether the frequency spectrograph (6) is flat in a B3 frequency band after the signals are stable, and recording the frequency characteristics of the frequency spectrograph if abnormal interference signal wave peaks exist; recording in-band noise power if no interference exists; repeating the measurement for 3 times, and calculating and solving a noise average power value P0 dBm;
s15, the calculation carrier forwards the Beidou signal power value P, and the calculation formula is as follows: P-P0-G- (-101) + (-130) + L-P0-G + L-29 dBm;
s16, comparing the power value P of the Beidou signal forwarded by the aircraft obtained through calculation with a design index, and judging whether the power value P meets the design index;
the specific test method for the time delay test of the Beidou signal transmission link of the aircraft comprises the following steps:
s21, setting a Beidou B3 active antenna (8) away from the test carrier;
s22, setting an amplification gain G dBm of a low-noise signal amplifier (5);
s23, the carrier transmits the Beidou satellite signals and the Beidou B3 active antenna (8) signals and simultaneously accesses the time delay test equipment (7);
s24, measuring the phase difference of two paths of pulse per second of the Beidou satellite signal and the Beidou B3 active antenna (8) signal transmitted by the carrier, repeatedly measuring for three times, and calculating the average value T of the phase difference, namely the time delay of the Beidou satellite signal transmitted by the carrier;
s25, comparing the calculated time delay T of the Beidou signal transmission link of the aircraft with a design index, and judging whether the design index is met;
the specific test method for the missile-borne Beidou signal processing module comprises the following steps:
s31, setting a Beidou B3 active antenna (8) away from the test carrier;
s32, the checking and calibration measurement carrier forwards Beidou satellite signals and Beidou B3 active antenna (8) signals, and the two paths of signals are guaranteed to work normally;
s33, the carrier transmits Beidou satellite signals and Beidou B3 active antenna (8) signals and simultaneously accesses the missile-borne Beidou signal processing module (9); wherein the carrier forwards Beidou satellite signals and accesses to a forwarding signal receiving port, and Beidou B3 active antenna (8) signals are accessed to a missile-borne receiver signal receiving port;
s34, connecting the missile-borne Beidou signal processing module (9) and the receiver testing equipment (10) through a testing cable;
s35, the airborne Beidou antenna (1) and the active power distributor (2) are powered on and started; the missile-borne Beidou signal processing module (9) is set to be in a hanging flight mode through the receiver testing equipment (10);
s36, controlling the missile-borne Beidou signal processing module (9) to be in cold start through the receiver testing equipment (10), and automatically recording the cold start time, the satellite receiving number, the satellite signal-to-noise ratio of the missile-borne Beidou signal processing module (9) and the channel AD power data by the receiver testing equipment (10); meanwhile, the positioning precision, the speed measurement precision, the pseudo range precision and the pseudo range precision are measured and analyzed by using the receiver test equipment (10);
s37, the missile-borne Beidou signal processing module (9) is set to be in an autonomous flight mode through the receiver testing equipment (10), the receiver testing equipment (10) automatically records recapture positioning time when the missile-borne Beidou signal processing module (9) forwards a Beidou satellite signal from an aerial carrier and switches to a Beidou B3 active antenna (8) signal, and when a simulated missile is separated from the aerial carrier, the Beidou satellite signal is switched to the response speed and the reliability of the missile-borne positioning receiver and the missile-borne Beidou signal processing module (9).
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6411797B1 (en) * | 1996-09-20 | 2002-06-25 | Itt Manufacturing Enterprises, Inc. | Method and apparatus for performance characterization of satellite transponders |
| CN102647223A (en) * | 2012-03-26 | 2012-08-22 | 北京空间飞行器总体设计部 | An Absolute Delay Calibration Method for Navigation Satellite Inter-satellite Link Antennas |
| CN103338086A (en) * | 2013-07-10 | 2013-10-02 | 航天恒星科技有限公司 | Testing system for radio frequency consistency of satellite mobile communication terminal and testing method of testing system |
| CN105659933B (en) * | 2010-12-08 | 2013-10-23 | 北京空间飞行器总体设计部 | The method of testing of the absolute time delay of a kind of satellite repeater |
| CN103472735A (en) * | 2013-09-24 | 2013-12-25 | 中国航空工业集团公司沈阳飞机设计研究所 | Automatic testing system of avionics system |
-
2019
- 2019-10-30 CN CN201911044488.7A patent/CN110823019B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6411797B1 (en) * | 1996-09-20 | 2002-06-25 | Itt Manufacturing Enterprises, Inc. | Method and apparatus for performance characterization of satellite transponders |
| CN105659933B (en) * | 2010-12-08 | 2013-10-23 | 北京空间飞行器总体设计部 | The method of testing of the absolute time delay of a kind of satellite repeater |
| CN102647223A (en) * | 2012-03-26 | 2012-08-22 | 北京空间飞行器总体设计部 | An Absolute Delay Calibration Method for Navigation Satellite Inter-satellite Link Antennas |
| CN103338086A (en) * | 2013-07-10 | 2013-10-02 | 航天恒星科技有限公司 | Testing system for radio frequency consistency of satellite mobile communication terminal and testing method of testing system |
| CN103472735A (en) * | 2013-09-24 | 2013-12-25 | 中国航空工业集团公司沈阳飞机设计研究所 | Automatic testing system of avionics system |
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