CN112968737A - System and method for self-closed loop test of carrier rocket wireless link and rocket - Google Patents
System and method for self-closed loop test of carrier rocket wireless link and rocket Download PDFInfo
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Abstract
The application relates to a system and a method for self-closed loop test of a carrier rocket wireless link and a rocket, and relates to the technical field of launch test of space rockets. In the uplink direction of the system, the ground remote equipment is used for sending a test instruction, the test terminal equipment receives the test instruction to generate a first test signal of a corresponding type, and the test antenna module is used for receiving the first test signal and transmitting the first test signal to the rocket functional receiving antenna; in the downlink direction, the test antenna module is used for receiving the second test signal of the corresponding type transmitted by the rocket-mounted functional transmitting antenna and transmitting the second test signal to the test terminal equipment, and the test terminal equipment receives the second test signal, demodulates the second test signal to generate corresponding total test result data and transmits the total test result data to the ground remote equipment. The self-closed loop test system for the carrier rocket wireless link solves the problems that in the related technology, the carrier rocket wireless link is low in test efficiency, poor in universality and expansibility and potential safety hazards exist.
Description
Technical Field
The application relates to the technical field of space launch testing, in particular to a system and a method for self-closed loop testing of a carrier rocket wireless link and a rocket.
Background
With the continuous development of aerospace technology, a carrier rocket test is an important component of rocket aerospace engineering, and has important functions of testing and researching the carrier rocket, making feasible argumentations on flight time sequence, control function and the like of the carrier rocket, evaluating the reliability of the carrier rocket, obtaining factors which are not beneficial to launching and the like. The wireless link test items of the launch vehicle specifically comprise telemetry, external test, remote control, satellite relay communication and the like, and are important test items which must be covered by the launch vehicle in a technical area and a launching field.
In the related technology, the test method mostly uses various ground test devices to respectively test different functional items of the carrier rocket, such as remote measurement, external test, remote control, satellite relay communication and the like, the test method needs various test devices and antennas during testing, a plurality of operating posts are correspondingly needed to be arranged, the test preparation and data acquisition and interpretation time is long, the types of the devices are various, the cable connection relationship is complex, and the whole system is long in time consumption when being unfolded and laid; and part of test equipment and antennas of the launching pad also need to be withdrawn before launching, so that personnel safety risks exist, and the requirements of future quick test and quick launching cannot be met.
Disclosure of Invention
The embodiment of the application provides a system and a method for self-closed loop test of a carrier rocket wireless link and a rocket, and aims to solve the problems of low wireless link test efficiency, poor universality and expansibility and potential safety hazards in the related technology.
In a first aspect, a system for self-closed loop testing of a launch vehicle wireless link is provided, which includes: the system comprises ground remote equipment, test terminal equipment and a test antenna module, wherein the test terminal equipment is used for being installed at the tail section of a carrier rocket and is connected with the ground remote equipment; wherein the content of the first and second substances,
in an uplink direction, the ground remote device is used for sending a test instruction, the test terminal device is used for receiving the test instruction to generate a first test signal of a corresponding type, and the test antenna module is used for receiving the first test signal and transmitting the first test signal to the rocket function receiving antenna;
in the downlink direction, the test antenna module is configured to receive a second test signal of a corresponding type transmitted by the rocket-mounted functional transmitting antenna, so as to process the second test signal and transmit the second test signal to the test terminal device, where the second test signal includes test result data generated after a test is performed on a terminal to be tested of a corresponding type on the launch vehicle according to the corresponding first test signal, and the test terminal device receives the second test signal, demodulates the second test signal, generates corresponding total test result data, and transmits the corresponding total test result data to the ground remote device.
In some embodiments, the test terminal device includes an integrated radio frequency module and a network conversion module, the integrated radio frequency module is connected to the test antenna module, and the network conversion module is disposed between the ground remote device and the integrated radio frequency module and respectively connected to the ground remote device and the integrated radio frequency module; wherein the content of the first and second substances,
in the uplink direction, the network conversion module is used for receiving the test instruction, and the comprehensive radio frequency module is used for receiving the test instruction transmitted by the network conversion module and generating a first test signal of a corresponding type according to the test instruction;
in the downlink direction, the integrated radio frequency module is configured to receive the second test signal of the corresponding type transmitted by the test antenna module and demodulate the second test signal, and the network conversion module is configured to receive the demodulated second test signal and assemble and frame the demodulated second test signal to generate corresponding test result data and transmit the test result data to the ground remote device.
In some embodiments, the integrated radio frequency module includes a digital unit and a radio frequency unit, the digital unit is connected to the network conversion module, and the radio frequency unit is connected to the test antenna module; wherein the content of the first and second substances,
in the uplink direction, the digital unit is configured to receive the test instruction and generate a corresponding baseband signal according to a signal format of the test instruction, and the radio frequency unit receives the baseband signal and performs up-conversion processing on the baseband signal to generate the first test signal of the corresponding type;
in the downlink direction, the radio frequency unit is used for receiving a second test signal of a corresponding type transmitted by the test antenna module and performing down-conversion processing on the second test signal, and the digital unit is used for receiving the second test signal after down-conversion processing so as to interpret the signal strength and the state of the second test signal, and is also used for mediating the second test signal into a corresponding code stream and transmitting the interpreted result and the corresponding code stream to the network conversion module.
In some embodiments, the test antenna module comprises:
the test transmitting antenna is used for receiving the first test signal transmitted by the radio frequency unit and transmitting the first test signal to the rocket function receiving antenna;
and the test receiving antenna is used for receiving a second test signal of a corresponding type transmitted by the rocket-mounted functional transmitting antenna, filtering and amplifying the second test signal and transmitting the second test signal to the radio frequency unit, wherein the second test signal comprises test result data generated after a terminal to be tested of a corresponding type on the carrier rocket is tested according to the corresponding first test signal.
In some embodiments, the first test signal is an external pulse radio frequency signal, a space-based remote radio frequency signal, or a satellite relay communication radio frequency signal, and the second test signal is an external pulse radio frequency signal, a space-based telemetry radio frequency signal, or a ground-based telemetry radio frequency signal.
In some embodiments, the test antenna module comprises:
the first transceiving antenna is used for receiving the external pulse radio-frequency signals transmitted by the radio-frequency unit and radiating the external pulse radio-frequency signals to the rocket-mounted function receiving antenna, the first transceiving antenna is also used for receiving the external pulse radio-frequency signals transmitted by the rocket-mounted function transmitting antenna and transmitting the external pulse radio-frequency signals transmitted by the rocket-mounted function transmitting antenna to the radio-frequency unit, and the external pulse radio-frequency signals transmitted by the rocket-mounted function transmitting antenna are generated again after the terminal to be tested of the corresponding type on the carrier rocket is tested according to the received external pulse radio-frequency signals;
and the second transceiving antenna is used for receiving the space-based remote control radio-frequency signal or the satellite relay communication radio-frequency signal transmitted by the radio-frequency unit, transmitting the space-based remote control radio-frequency signal or the satellite relay communication radio-frequency signal to the rocket-mounted functional receiving antenna, receiving the space-based telemetry radio-frequency signal or the ground-based telemetry radio-frequency signal transmitted by the rocket-mounted functional transmitting antenna, and transmitting the space-based telemetry radio-frequency signal or the ground-based telemetry radio-frequency signal to the radio-frequency unit.
In some embodiments, the test terminal device further includes a power supply module, and the power supply module is connected to the digital unit, the radio frequency unit, and the network conversion module.
In a second aspect, a method for self-closed loop test of a launch vehicle wireless link is provided, which includes the steps of:
sending a test instruction, generating a first test signal of a corresponding type according to the test instruction, transmitting the first test signal to an arrow functional receiving antenna, and transmitting the first test signal to a terminal to be tested of the corresponding type through the arrow functional receiving antenna to test;
and sequentially transmitting a second test signal of a corresponding type including test result data generated after the terminal to be tested tests according to the corresponding first test signal through the test antenna module and the test terminal equipment, and demodulating the second test signal to generate total test result data and then transmitting the total test result data to the ground far-end equipment.
In a third aspect, there is provided a rocket comprising: the rocket comprises the system for the self-closed loop test of the wireless link of the carrier rocket.
In some embodiments, the system is disposed on the tail section of the rocket, the test transmitting antenna and the test receiving antenna are disposed on the inclined conical surface of the tail wing of the rocket, the mounting position of the test transmitting antenna corresponds to the mounting position of the functional receiving antenna on the rocket, and the mounting position of the test receiving antenna corresponds to the mounting position of the functional transmitting antenna on the rocket.
The beneficial effect that technical scheme that this application provided brought includes:
the embodiment of the application provides a system for self-closed loop test of a wireless link of a carrier rocket, which is characterized in that ground remote equipment, test terminal equipment and a test antenna module are arranged to carry out miniaturization and integration design on ground test equipment for testing the wireless link of the carrier rocket, replace most test equipment and all test equipment of a launching site in an original technical area, cancel all front-end post settings required by wireless link test and effectively reduce the safety risk of operators; the test system can automatically and quickly complete each function test according to the instruction of the ground remote equipment, greatly shortens the launch test time of the rocket, simplifies the test flow and greatly improves the test efficiency; by the aid of modular design and software radio technology, the rocket single machine is high in universality and expandability, and flexible configuration can be achieved according to different types of carrier rocket wireless link test items.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings needed to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
Fig. 1 is a block diagram of a system for self-closed loop testing of a launch vehicle wireless link according to an embodiment of the present application;
FIG. 2 is a schematic transmission path diagram of a system for self-closed loop testing of a carrier rocket wireless link according to an embodiment of the present disclosure;
fig. 3 is a schematic diagram of a rocket including a system for self-closed loop testing of a launch vehicle wireless link according to an embodiment of the present application.
In the figure: the method comprises the following steps of 1-ground remote equipment, 2-test terminal equipment, 20-comprehensive radio frequency module, 200-radio frequency unit, 201-digital unit, 21-network conversion module, 22-power supply module, 3-test antenna module, 30-test transmitting antenna, 31-test receiving antenna, 4-rocket-based functional receiving antenna and 5-rocket-based functional transmitting antenna.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some embodiments of the present application, but not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
The embodiment of the application provides a system for self-closed loop test of a carrier rocket wireless link, which can solve the problems of low wireless link test efficiency, poor universality and expansibility and potential safety hazard in the related technology.
Referring to fig. 1 and 2, the system for self-closed loop test of the wireless link of the launch vehicle comprises a ground remote device 1, a test terminal device 2 and a test antenna module 3, wherein the test terminal device 2 is arranged at the tail section of the launch vehicle and connected with the ground remote device 1; when the self-closed loop test system works, the signal flow direction is divided into an uplink flow direction and a downlink flow direction, in the uplink direction, the ground far-end device 1 is used for sending a test instruction, the test terminal device 2 is used for receiving the test instruction to generate a first test signal of a corresponding type, and the test antenna module 3 is used for receiving the first test signal and transmitting the first test signal to the rocket function receiving antenna 4; in the downlink direction, the test antenna module 3 is configured to receive a second test signal of a corresponding type transmitted by the rocket-mounted functional transmitting antenna 5, so as to process the second test signal and transmit the second test signal to the test terminal device 2, where the second test signal includes test result data generated after a test is performed on a terminal to be tested of a corresponding type on the launch vehicle according to the corresponding first test signal, and the test terminal device 2 receives the second test signal, demodulates the second test signal to generate corresponding total test result data, and transmits the total test result data to the ground remote device 1. The ground remote equipment 1 comprises an optical switch and a remote control terminal, and the optical switch and the remote control terminal are connected through a network cable.
Specifically, after the system for the self-closed loop test of the wireless link of the carrier rocket launches the test instruction, the test terminal device 2 receives the test instruction and generates a first test signal of a corresponding type, and then transmits the first test signal to the function receiving antenna 4 on the rocket through the test antenna module 3, the process is used for testing the receiving performance of a plurality of terminals to be tested of the corresponding type on the carrier rocket, meanwhile, the terminals to be tested of the corresponding type can launch second test signals of the corresponding type to the test antenna module 3, and the purpose is to test the launching performance of the plurality of terminals to be tested of the corresponding type. Here, the test of the receiving performance and the transmitting performance are two relatively independent processes, however, the second test signal includes test result data generated after the corresponding kind of terminal to be tested performs the test according to the corresponding first test signal, so as to feed back the test result of the receiving performance to the ground remote device 1.
Further, the testing terminal device 2 specifically includes an integrated radio frequency module 20 and a network conversion module 21, the integrated radio frequency module 20 is connected to the testing antenna module 3, and the network conversion module 21 is disposed between the ground remote device 1 and the integrated radio frequency module 20 and is respectively connected to the ground remote device 1 and the integrated radio frequency module 20; in the uplink direction, the network conversion module 21 is configured to receive a test instruction, and the integrated radio frequency module 20 is configured to receive the test instruction transmitted by the network conversion module 21, and generate a first test signal of a corresponding type according to the test instruction; in the downlink direction, the integrated radio frequency module 20 is configured to receive the second test signal of the corresponding type transmitted by the test antenna module 3, and demodulate the second test signal, the network conversion module 21 is configured to receive the demodulated second test signal, and aggregate and frame the demodulated second test signal, so as to generate corresponding total test result data and transmit the total test result data to the ground remote device 1, and the network conversion module 21 is mainly configured to be responsible for data interaction, and is connected to the ground remote device 1 through an optical fiber network by using an optical fiber communication method, so that the total test result data has a high external transmission rate and a large transmission capacity.
Further, the integrated rf module 20 includes a digital unit 201 and an rf unit 200, where the digital unit 201 is connected to the network switching module 21, and the rf unit 200 is connected to the test antenna module 3. In the uplink direction, the digital unit 201 is configured to receive a test instruction and generate a corresponding baseband signal according to a signal format of the test instruction, and the radio frequency unit 200 receives the baseband signal and performs up-conversion processing on the baseband signal to generate a first test signal of a corresponding type; in the downlink direction, the radio frequency unit 200 is configured to receive a second test signal of a corresponding type transmitted by the test antenna module 3, and perform down-conversion processing on the second test signal, the digital unit 201 is configured to receive the second test signal after down-conversion processing to interpret the signal strength and state thereof, and further is configured to mediate the second test signal into a corresponding code stream, and transmit both the interpretation result and the corresponding code stream to the network conversion module 21, and the network conversion module 21 performs aggregation and framing on the second test signal to generate corresponding total test result data and transmit the total test result data to the ground remote device 1.
Further, there may be two types of forms of the test antenna module 3, one is in a dual-frequency mode, and the other is in a single-frequency mode. When the dual-frequency mode is adopted, the test antenna module 3 includes a test transmitting antenna 30 and a test receiving antenna 31, the test transmitting antenna 30 is configured to receive a first test signal transmitted by the radio frequency unit 200 and transmit the first test signal to the rocket-mounted function receiving antenna 4, and the test receiving antenna 31 is configured to receive a second test signal of a corresponding type transmitted by the rocket-mounted function transmitting antenna 5, filter and amplify the second test signal, and transmit the second test signal to the radio frequency unit 200. Specifically, each of the test transmitting antenna 30 and the test receiving antenna 31 has only a function of receiving or transmitting a signal, but it covers a wider frequency range than a single-frequency antenna, and can receive or transmit a plurality of signals having different frequencies. The number and layout of the test transmitting antennas 30 and the test receiving antennas 31 are designed by comprehensively considering the layout of the functional antennas on the arrow, the transmitting power and the receiving gain of the functional antennas on the arrow, and other factors.
Specifically, the first test signal is an external test pulse radio frequency signal, a space-based remote control radio frequency signal, a satellite relay communication radio frequency signal, or the like, the second test signal is an external test pulse radio frequency signal, a space-based remote control radio frequency signal, a foundation remote control radio frequency signal, or the like, the flow direction of the external test pulse radio frequency signal, the space-based remote control radio frequency signal, or the foundation remote control radio frequency signal is a downlink flow direction, the downlink flow direction signal generally includes but is not limited to the above signals, and the flow direction of the corresponding external test pulse radio frequency signal, the space-based remote control radio frequency signal, or the satellite relay communication radio frequency signal is an uplink flow direction, and the uplink flow direction signal.
Specifically, the space-based remote control radio frequency signal corresponds to the space-based remote measurement radio frequency signal, and this correspondence means that corresponding test result data generated by the corresponding terminal to be tested after testing is performed according to the received space-based remote measurement radio frequency signal is fed back to the ground remote equipment 1 through the space-based remote measurement radio frequency signal; in addition, the ground-based telemetry radio frequency signal is only used for a transmission performance test, and test result data corresponding to the satellite relay communication radio frequency signal is also fed back to the ground remote equipment 1 through the ground-based telemetry radio frequency signal.
When a single-frequency mode is adopted, the test antenna module 3 comprises a first transceiving antenna and a second transceiving antenna, the first transceiving antenna is used for receiving the external pulse radio-frequency signal transmitted by the radio-frequency unit 200 and radiating the external pulse radio-frequency signal to the rocket-mounted functional receiving antenna 4, the first transceiving antenna is also used for receiving the external pulse radio-frequency signal transmitted by the rocket-mounted functional transmitting antenna 5 and transmitting the external pulse radio-frequency signal transmitted by the rocket-mounted functional transmitting antenna 5 to the radio-frequency unit 200, and the external pulse radio-frequency signal transmitted by the rocket-mounted functional transmitting antenna 5 is generated again after a terminal to be tested of a corresponding type on a carrier rocket is tested according to the received external pulse radio-frequency signal; the second transceiving antenna is used for receiving space-based remote control radio frequency signals or satellite relay communication radio frequency signals transmitted by the radio frequency unit 200, radiating the space-based remote control radio frequency signals or satellite relay communication radio frequency signals to the rocket-mounted functional receiving antenna 4, receiving space-based telemetry radio frequency signals or ground-based telemetry radio frequency signals transmitted by the rocket-mounted functional transmitting antenna 5, and transmitting the space-based telemetry radio frequency signals or ground-based telemetry radio frequency signals to the radio frequency unit 200. Compared with a dual-frequency antenna, a single-frequency antenna is more beneficial to the isolation and filtering design of radio-frequency signals.
Further, the test terminal device 2 further includes a power module 22, where the power module 22 is connected to the digital unit 201, the radio frequency unit 200, and the network conversion module 21, and is used for inputting external power and supplying internal power to the digital unit 201, the radio frequency unit 200, and the network conversion module 21.
The application also provides a self-closed loop test method of the carrier rocket wireless link, which comprises the steps of firstly sending a test instruction, generating a first test signal of a corresponding type according to the test instruction, transmitting the first test signal to the rocket-mounted functional receiving antenna 4, and transmitting the first test signal to a terminal to be tested of the corresponding type through the rocket-mounted functional receiving antenna 4 for testing; and sequentially transmitting a second test signal of a corresponding type including test result data generated after the terminal to be tested of a corresponding type is tested according to the corresponding first test signal through the test antenna module 3 and the test terminal equipment 2, and demodulating the second test signal to generate total test result data and then transmitting the total test result data to the ground far-end equipment 1.
Specifically, taking space-based remote control radio frequency signal transmission as an example, firstly, a space-based remote control function test instruction is transmitted through the ground remote device 1, after the network conversion module 21 receives the space-based remote control function test instruction from the ground, the instruction is sent to the digital unit 201 in the integrated radio frequency module 20, the digital unit 201 starts to respond to the instruction after receiving the instruction, and starts to generate a corresponding baseband signal according to a space-based remote control baseband signal format, the radio frequency unit 200 receives the baseband signal and performs up-conversion and modulation processing on the baseband signal to generate a space-based remote control radio frequency signal, the space-based remote control radio frequency signal is amplified by the test transmitting antenna 30 and radiated in the arrow head direction, since the on-arrow function receiving antenna 4 is located in the arrow head direction, here the on-arrow function receiving antenna 4 is a generic term, the antenna specifically comprises an arrow antenna remote control receiving antenna, an arrow external measuring receiving antenna, a satellite communication receiving antenna and the like. After the space-based remote control receiving antenna receives the space-based remote control radio frequency signal transmitted by the test transmitting antenna 30, the space-based remote control receiving antenna transmits the radio frequency signal to a space-based test terminal to be tested, the space-based measurement and control terminal performs related tests according to the space-based remote control radio frequency signal and generates corresponding test result data according to a response result, and the test result data is finally transmitted to the ground remote equipment 1 through the space-based remote control radio frequency signal to complete the test of the space-based remote control function.
Taking space-based telemetering radio-frequency signal reception as an example, a space-based telemetering transmitting antenna on a rocket amplifies space-based telemetering radio-frequency signals to radiate outwards to test transmitting performance or feed back corresponding test result data, a test receiving antenna 31 installed at a tail section of the rocket receives the space-based telemetering radio-frequency signals and then carries out filtering and amplification, firstly, a radio-frequency unit 200 receives the space-based telemetering radio-frequency signals transmitted by a test antenna module 3 and carries out down-conversion processing on the space-based telemetering radio-frequency signals, a digital unit 201 receives the space-based telemetering radio-frequency signals after down-conversion processing to judge main results such as signal strength and locking state, the digital unit is also used for mediating the radio-frequency signals into corresponding code streams, the judging results and the corresponding code streams are both transmitted to a network conversion module 21, the network conversion module 21 carries out convergence and framing on the code streams to generate corresponding space-based telemetering network data packets, and then transmits the space-based telemetering network data packets to a ground remote device 1 through, and the ground remote equipment 1 analyzes and comprehensively interprets the total test result data to complete the detection of the space-based remote function.
The transmitting of the external pulse radio frequency signal and the satellite relay communication radio frequency signal is the same as the space-based remote control radio frequency signal, and the receiving of the external pulse radio frequency signal and the ground-based remote control radio frequency signal is the same as the space-based remote control radio frequency signal.
The application also provides a rocket, which is shown in fig. 3 and comprises the system for the self-closed loop test of the wireless link of the carrier rocket. Further, the system for the self-closed loop test of the wireless link of the carrier rocket is arranged on the tail section of the rocket, specifically, the test transmitting antenna 30 and the test receiving antenna 31 are arranged on the inclined conical surface of the tail wing of the rocket, the installation position of the test transmitting antenna 30 corresponds to the installation position of the function receiving antenna 4 on the rocket, the installation position of the test receiving antenna 31 corresponds to the installation position of the function transmitting antenna 5 on the rocket, the gain of the function transmitting antenna in the arrow head direction is improved, the signal strength is enhanced, and the receiving and the transmitting of signals are ensured. The system is arranged on the tail section of the rocket and is connected with the ground remote equipment 1 on the ground through optical fiber and rocket tail section release and insertion.
The influence on the carrying capacity of the rocket can be ignored, or the existing single machine hardware on the rocket is reused by using the software radio technology without adding hardware.
In the description of the present application, it should be noted that the terms "upper", "lower", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, which are only for convenience in describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and operate, and thus, should not be construed as limiting the present application. Unless expressly stated or limited otherwise, the terms "mounted," "connected," and "connected" are intended to be inclusive and mean, for example, that they may be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.
It is noted that, in the present application, relational terms such as "first" and "second", and the like, are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.
The above description is merely exemplary of the present application and is presented to enable those skilled in the art to understand and practice the present application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the application. Thus, the present application is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (10)
1. A system for self-closed loop testing of a launch vehicle wireless link, comprising: the test system comprises ground remote equipment (1), test terminal equipment (2) and a test antenna module (3), wherein the test terminal equipment (2) is used for being installed at the tail section of a carrier rocket and is connected with the ground remote equipment (1); wherein the content of the first and second substances,
in the uplink direction, the ground remote equipment (1) is used for sending a test instruction, the test terminal equipment (2) is used for receiving the test instruction to generate a first test signal of a corresponding type, and the test antenna module (3) is used for receiving the first test signal and transmitting the first test signal to the rocket function receiving antenna (4);
in the downlink direction, the test antenna module (3) is configured to receive a second test signal of a corresponding type transmitted by the rocket-mounted functional transmitting antenna (5) to process the second test signal and transmit the second test signal to the test terminal device (2), the second test signal includes test result data generated after a test is performed on a terminal to be tested of a corresponding type on the launch vehicle according to the corresponding first test signal, and the test terminal device (2) receives the second test signal and demodulates the second test signal to generate corresponding total test result data and transmits the total test result data to the ground remote device (1).
2. The system for self-closed loop testing of a launch vehicle wireless link of claim 1, wherein: the testing terminal device (2) comprises a comprehensive radio frequency module (20) and a network conversion module (21), the comprehensive radio frequency module (20) is connected with the testing antenna module (3), and the network conversion module (21) is arranged between the ground far-end device (1) and the comprehensive radio frequency module (20) and is respectively connected with the ground far-end device (1) and the comprehensive radio frequency module (20); wherein the content of the first and second substances,
in the uplink direction, the network conversion module (21) is configured to receive the test instruction, and the integrated radio frequency module (20) is configured to receive the test instruction transmitted by the network conversion module (21) and generate a first test signal of a corresponding type according to the test instruction;
in the downlink direction, the integrated radio frequency module (20) is configured to receive the second test signal of the corresponding type transmitted by the test antenna module (3), and demodulate the second test signal, and the network conversion module (21) is configured to receive the demodulated second test signal, and assemble and frame the demodulated second test signal, so as to generate the corresponding test result data, and transmit the test result data to the ground remote device (1).
3. The system for self-closed loop testing of a launch vehicle wireless link of claim 2, wherein: the comprehensive radio frequency module (20) comprises a digital unit (201) and a radio frequency unit (200), the digital unit (201) is connected with a network conversion module (21), and the radio frequency unit (200) is connected with the test antenna module (3); wherein the content of the first and second substances,
in the uplink direction, the digital unit (201) is configured to receive the test instruction and generate a corresponding baseband signal according to a signal format of the test instruction, and the radio frequency unit (200) receives the baseband signal and performs up-conversion processing on the baseband signal to generate the first test signal of a corresponding type;
in the downlink direction, the radio frequency unit (200) is configured to receive a second test signal of a corresponding type transmitted by the test antenna module (3), and perform down-conversion processing on the second test signal, and the digital unit (201) is configured to receive the second test signal after down-conversion processing to interpret the signal strength and state thereof, and is further configured to mediate the second test signal into a corresponding code stream, and transmit both the interpretation result and the corresponding code stream to the network conversion module (21).
4. A system for self-closed loop testing of a launch vehicle radio link according to claim 3, characterised in that the test antenna module (3) comprises:
a test transmitting antenna (30) for receiving the first test signal transmitted by the radio frequency unit (200) and for transmitting the first test signal to the rocket-functional receiving antenna (4);
the test receiving antenna (31) is used for receiving a second test signal of a corresponding type transmitted by the rocket-mounted functional transmitting antenna (5), filtering and amplifying the second test signal and transmitting the second test signal to the radio frequency unit (200), wherein the second test signal comprises test result data generated after a terminal to be tested of a corresponding type on the carrier rocket tests according to the corresponding first test signal.
5. A system for self-closed loop testing of a launch vehicle radio link, as defined in claim 3, wherein: the first test signal is an external test pulse radio frequency signal, a space-based remote control radio frequency signal or a satellite relay communication radio frequency signal, and the second test signal is an external test pulse radio frequency signal, a space-based remote control radio frequency signal or a ground-based remote control radio frequency signal.
6. A system for self-closed loop testing of a launch vehicle radio link according to claim 5, characterised in that the test antenna module (3) comprises:
the first transceiving antenna is used for receiving the external pulse radio-frequency signals transmitted by the radio-frequency unit (200) and radiating the external pulse radio-frequency signals to the rocket-mounted function receiving antenna (4), the first transceiving antenna is also used for receiving the external pulse radio-frequency signals transmitted by the rocket-mounted function transmitting antenna (5) and transmitting the external pulse radio-frequency signals transmitted by the rocket-mounted function transmitting antenna (5) to the radio-frequency unit (200), and the external pulse radio-frequency signals transmitted by the rocket-mounted function transmitting antenna (5) are generated again after the terminal to be tested of the corresponding type on the carrier rocket is tested according to the received external pulse radio-frequency signals;
a second transceiving antenna for receiving the space-based remote control radio frequency signal or satellite relay communication radio frequency signal transmitted via the radio frequency unit (200), for transmitting the space-based remote control radio frequency signal or satellite relay communication radio frequency signal to the rocket-mounted function receiving antenna (4), for receiving the space-based telemetry radio frequency signal or ground-based telemetry radio frequency signal transmitted via the rocket-mounted function transmitting antenna (5), and for transmitting the space-based telemetry radio frequency signal or ground-based telemetry radio frequency signal to the radio frequency unit (200).
7. A system for self-closed loop testing of a launch vehicle radio link, as defined in claim 3, wherein: the test terminal equipment (2) further comprises a power supply module (22), and the power supply module (22) is connected with the digital unit (201), the radio frequency unit (200) and the network conversion module (21).
8. A method for self-closed loop test of a carrier rocket wireless link is characterized by comprising the following steps:
sending a test instruction, generating a first test signal of a corresponding type according to the test instruction, transmitting the first test signal to an arrow functional receiving antenna (4), and transmitting the first test signal to a terminal to be tested of the corresponding type through the arrow functional receiving antenna (4) for testing;
and sequentially transmitting a second test signal of a corresponding type including test result data generated after the terminal to be tested tests according to the corresponding first test signal through the test antenna module (3) and the test terminal equipment (2), and demodulating the second test signal to generate total test result data and then transmitting the total test result data to the ground far-end equipment (1).
9. A rocket, characterized in that it comprises: the rocket including a system for self-closed loop testing of launch vehicle wireless links according to claims 1-8.
10. A rocket as recited in claim 9, wherein: the system is arranged on the tail section of the rocket, the test transmitting antenna (30) and the test receiving antenna (31) are arranged on the inclined conical surface of the tail wing of the rocket, the mounting position of the test transmitting antenna (30) corresponds to the mounting position of the function receiving antenna (4) on the rocket, and the mounting position of the test receiving antenna (31) corresponds to the mounting position of the function transmitting antenna (5) on the rocket.
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| CN202110158707.5A CN112968737B (en) | 2021-02-04 | 2021-02-04 | System and method for self-closed loop test of carrier rocket wireless link and rocket |
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Cited By (1)
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| CN117255036A (en) * | 2023-11-20 | 2023-12-19 | 中国西安卫星测控中心 | Link connectivity checking method, device and equipment of multi-target measurement and control system |
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