CN112082436B - Carrier rocket remote measuring system - Google Patents
Carrier rocket remote measuring system Download PDFInfo
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- CN112082436B CN112082436B CN202010812912.4A CN202010812912A CN112082436B CN 112082436 B CN112082436 B CN 112082436B CN 202010812912 A CN202010812912 A CN 202010812912A CN 112082436 B CN112082436 B CN 112082436B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/01—Arrangements thereon for guidance or control
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B35/00—Testing or checking of ammunition
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
- G05B19/042—Programme control other than numerical control, i.e. in sequence controllers or logic controllers using digital processors
- G05B19/0423—Input/output
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Abstract
The application provides a launch vehicle telemetry system, comprising: an rocket-borne telemetry module and a ground control module; the rocket-borne telemetry module comprises a data acquisition device and is connected with the ground control module through an optical fiber link; the ground control module is used for sending a control command to the rocket-borne telemetry module; the rocket-borne remote measuring module is used for acquiring a control instruction, controlling the data acquisition device to acquire corresponding detection data according to the control instruction, and transmitting the detection data to the ground control module based on the optical fiber link; and the ground control module is also used for acquiring detection data, detecting the carrier rocket according to the detection data and generating a detection result. The data acquisition device can be controlled to acquire the currently required detection data through the control instruction, the data transmission pressure is reduced, the data transmission efficiency is improved, the detection data in the system are transmitted based on the optical fiber link, the transmission speed is high, and the data transmission efficiency is further improved.
Description
Technical Field
The invention relates to the field of rocket telemetry, in particular to a carrier rocket telemetry system.
Background
At present, in order to ensure the safety of the carrier rocket, strict safety detection needs to be carried out on the carrier rocket before launching.
In the prior art, a data acquisition device on a carrier rocket is generally used for acquiring detection data of the carrier rocket, packaging and framing a large amount of detection data, and transmitting the detection data to a ground repeater through an RS-422 circuit; shaping the packed and framed detection data based on a ground repeater, and transmitting the detection data to a protocol converter through an RS-422 circuit; the protocol converter is used for converting the communication protocol of the communication equipment to a communication protocol compatible with the ground controller; and finally, sending the detection data after the protocol conversion to a ground controller, and carrying out safety detection on the carrier rocket by the ground controller according to the received detection data.
However, in the prior art, as the research and development technology of the launch vehicle is continuously improved, the complexity of the security detection is also continuously improved, and more detection data need to be acquired by the data acquisition device, the data transmission pressure is higher, and the data transmission efficiency is lower. Therefore, a telemetry system capable of reducing data transmission pressure is urgently needed, and has an important significance for improving data transmission efficiency.
Disclosure of Invention
Therefore, the technical problem to be solved by the invention is to overcome the defects of high data transmission pressure and low data transmission rate in the prior art, thereby providing a remote measuring system of a carrier rocket.
The present application provides a launch vehicle telemetry system, comprising: the rocket-borne telemetry module and the ground control module; the rocket-borne telemetry module comprises a data acquisition device, and is connected with the ground control module through an optical fiber link;
the ground control module is used for sending a control instruction to the rocket-borne telemetry module;
the rocket-borne telemetry module is used for acquiring the control instruction, controlling a data acquisition device to acquire corresponding detection data according to the control instruction, and sending the detection data to the ground control module based on the optical fiber link;
the ground control module is further configured to acquire the detection data, detect the carrier rocket according to the detection data, and generate a detection result.
Optionally, the rocket-borne telemetry module comprises a self-detection device;
the self-detection device is used for acquiring the detection data, performing self-detection according to the detection data, generating a self-detection result and sending the self-detection result to the ground control module.
Optionally, the rocket-borne telemetry module further comprises a parameter configuration device;
the ground control module is also used for sending a configuration parameter instruction to the rocket-borne telemetry module;
and the parameter configuration device is used for adjusting the configuration parameters of the carrier rocket according to the configuration parameter instruction.
Optionally, the ground control module is further configured to:
and adjusting the configuration parameter instruction according to the detection result and/or the self-detection result.
Optionally, the ground control module is further configured to:
and acquiring a preset launching task requirement, and generating the configuration parameter instruction according to the preset launching task requirement.
Optionally, the ground control module is further configured to obtain a preset detection requirement, and generate the control instruction according to the preset detection requirement.
Optionally, the rocket-borne telemetry module and the ground control module both use an ethernet communication protocol.
Optionally, a unplugging connector is arranged on the optical fiber link;
and the unplugging connector is used for receiving a unplugging signal sent by the ground control module when the carrier rocket is to be launched, and performing separation processing according to the unplugging signal so as to disconnect the optical fiber link.
Optionally, an optical fiber conversion head is arranged on an optical fiber link between the unplugging connector and the ground control module;
the optical fiber conversion head is used for isolating the tail flame of the carrier rocket during launch of the carrier rocket.
Optionally, the rocket-borne telemetry module comprises a first signal conversion device, and the surface control module comprises a second signal conversion device;
the second signal conversion device is used for converting the control instruction in the form of a digital signal into a corresponding control instruction in the form of an optical signal and sending the control instruction in the form of the optical signal to the rocket-borne telemetry module;
the first signal conversion device is used for converting the control instruction in the form of the received optical signal into a control instruction in the form of a corresponding digital signal; converting the detection data in the form of digital signals into detection data in the form of corresponding optical signals, and sending the detection data in the form of the optical signals to the ground control module;
the second signal conversion device is further configured to convert the received detection data in the optical signal form into corresponding detection data in the digital signal form.
This application technical scheme has following advantage:
the application provides a launch vehicle telemetry system, comprising: the rocket-borne telemetry module and the ground control module; the rocket-borne telemetry module comprises a data acquisition device and is connected with the ground control module through an optical fiber link; the ground control module is used for sending a control command to the rocket-borne telemetry module; the rocket-borne telemetry module is used for acquiring a control instruction, controlling the data acquisition device to acquire corresponding detection data according to the control instruction, and sending the detection data to the ground control module based on the optical fiber link; and the ground control module is also used for acquiring detection data, detecting the carrier rocket according to the detection data and generating a detection result. The system that above-mentioned scheme provided can only transmit the detection data that the present needs at every turn through control command control data acquisition device collection present needs, has alleviateed data transmission pressure, has improved data transmission efficiency simultaneously, and the detection data in this system is based on that the optic fibre link carries out the transmission, and transmission speed is fast, has further improved data transmission efficiency.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments or the prior art descriptions will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art according to the drawings.
FIG. 1 is a schematic diagram of a prior art conventional launch vehicle telemetry system;
FIG. 2 is a schematic structural diagram of a launch vehicle telemetry system provided in an embodiment of the present application;
fig. 3 is a schematic structural diagram of an exemplary ethernet packet according to an embodiment of the present application;
FIG. 4 is a schematic diagram of another alternative launch vehicle telemetry system according to an embodiment of the present application;
FIG. 5 is a schematic diagram of a configuration of yet another launch vehicle telemetry system provided in an embodiment of the present application;
FIG. 6 is a schematic structural diagram of yet another launch vehicle telemetry system provided in accordance with an embodiment of the present application;
FIG. 7 is a schematic structural diagram of yet another launch vehicle telemetry system provided in an embodiment of the present application;
FIG. 8 is a schematic diagram of a configuration of yet another launch vehicle telemetry system provided in an embodiment of the present application.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be obtained by a person skilled in the art without making any creative effort based on the embodiments in the present invention, belong to the protection scope of the present invention.
Furthermore, the terms "first," "second," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or to implicitly indicate a number of the indicated technical features. In the description of the following examples, "plurality" means two or more unless specifically limited otherwise.
Fig. 1 is a schematic structural diagram of a conventional telemetry system for a launch vehicle, and fig. 1 shows that the conventional telemetry system for a launch vehicle can only realize unidirectional data transmission. The data acquisition device on the carrier rocket is usually used for acquiring all detection data of the carrier rocket, packaging and framing a large amount of detection data, and transmitting the detection data to the ground repeater through the RS-422 circuit; shaping the packed and framed detection data based on a ground repeater, and transmitting the detection data to a protocol converter through an RS-422 circuit; the protocol converter is used for converting the communication protocol of the communication equipment to a communication protocol compatible with the ground controller; and finally, sending the detection data after the protocol conversion is completed to a ground controller, and carrying out safety detection on the carrier rocket by the ground controller according to the received detection data. However, as the research and development technologies of the launch vehicle are continuously improved, the complexity of the safety detection is also continuously improved, and more detection data need to be acquired by the data acquisition device, the data transmission pressure is larger, and the data transmission efficiency is lower.
In view of the above problems, an embodiment of the present application provides a launch vehicle telemetry system, including: an rocket-borne telemetry module and a ground control module; the rocket-borne telemetry module comprises a data acquisition device, and is connected with the ground control module through an optical fiber link; the ground control module is used for sending a control command to the rocket-borne telemetry module; the rocket-borne telemetry module is used for acquiring a control instruction, controlling the data acquisition device to acquire corresponding detection data according to the control instruction, and sending the detection data to the ground control module based on the optical fiber link; and the ground control module is also used for acquiring detection data, detecting the carrier rocket according to the detection data and generating a detection result. The system that above-mentioned scheme provided can only transmit the detection data that the present needs at every turn through control command control data acquisition device collection present needs, has reduced data transmission pressure promptly, has improved data transmission efficiency simultaneously, and the detection data in this system is based on that the optic fibre link carries out the transmission, and transmission speed is fast, has further improved data transmission efficiency.
These several specific embodiments may be combined with each other below, and details of the same or similar concepts or processes may not be repeated in some embodiments. Embodiments of the present invention will be described below with reference to the accompanying drawings.
The embodiment of the application provides a carrier rocket telemetry system, which is used for solving the technical problems that the carrier rocket telemetry system in the prior art is high in data transmission pressure and low in data transmission efficiency.
As shown in fig. 2, a schematic structural diagram of a telemetry system for a launch vehicle is provided in an embodiment of the present application, where the telemetry system 20 includes: an rocket-borne telemetry module 201 and a ground control module 202; the rocket-borne telemetry module 201 comprises a data acquisition device 2011, and the rocket-borne telemetry module 201 is connected with the ground control module 202 through an optical fiber link 203.
The ground control module 202 is used for sending a control instruction to the rocket-borne telemetry module 201; the rocket-borne telemetry module 201 is used for acquiring a control instruction, controlling the data acquisition device 2011 to acquire corresponding detection data according to the control instruction, and sending the detection data to the ground control module 202 based on the optical fiber link 203; the ground control module 202 is further configured to obtain detection data, detect the carrier rocket according to the detection data, and generate a detection result.
It should be explained that the rocket-borne telemetry module 201 is located on a carrier rocket, wherein the detection data can be various mechanical and thermal environmental parameters, image and video parameters, working condition parameters of related devices, and the like of the carrier rocket.
Specifically, in an embodiment, the ground control module 202 is further configured to obtain a preset detection requirement, and generate a control instruction according to the preset detection requirement.
The preset detection requirement may include relevant information such as a detection type and a detection time.
In the process of detecting the carrier rocket, the detection data mainly comprises impact parameters, vibration parameters, noise parameters, temperature parameters, pressure parameters, heat flow parameters, video parameters, key equipment operation state parameters and the like. The data volume of the impact parameters, the vibration parameters and the noise parameters is large, and the impact parameters, the vibration parameters and the noise parameters do not need to be detected before the carrier rocket is launched. Therefore, in order to further reduce the data transmission pressure, the parameters may be selectively acquired, i.e., the impact parameter, the vibration parameter, and the noise parameter may not be acquired for the moment.
Specifically, in one embodiment, to further improve data transmission efficiency, both rocket-borne telemetry module 201 and surface control module 202 employ an ethernet communication protocol.
It should be explained that, in the prior art, the launch vehicle telemetry system usually adopts the PCM encoded sub-frame communication protocol, and the ground controller usually adopts the ethernet communication protocol, so before sending the detection data to the ground controller, the protocol converter is required to perform protocol conversion on the detection data under the PCM encoded sub-frame communication protocol, the protocol conversion operation mainly includes adding time code and data packet, and the like, the operation flow is complicated, which is not beneficial to ensuring the data transmission efficiency, and the reliability is low.
Specifically, the rocket-borne telemetry module 201 adopts the same communication protocol as the ground control module 202, so that the steps of protocol conversion can be reduced, the data transmission efficiency is improved, the reliability of data transmission is improved, and the ethernet communication protocol can realize the bidirectional data transmission between the rocket-borne telemetry module 201 and the ground control module 202.
Fig. 3 is a schematic structural diagram of an exemplary ethernet packet according to an embodiment of the present disclosure. The effective data area adopts a data structure commonly used by the ground control module 202 network, and comprises time codes, data packet types and telemetry full frames. The time code is used for identifying the relative time of the data acquisition framing moment in the telemetry full frame, so that data interpretation is facilitated; the type of the data packet is used for identifying data; the telemetry full frame is all data of a telemetry period, and the data packet is sent circularly by taking the time required by framing a telemetry full frame data acquisition as a period.
The optical fiber link 203 is a light transmission tool, that is, only the detection data in the form of optical signals can be transmitted, the detection data acquired by the data acquisition device 2011 is in the form of digital signals, the control instruction sent by the ground control module 202 is also in the form of digital signals, and the ground control module 202 can only identify the detection data in the form of digital signals.
In order to solve the above problems, specifically, in an embodiment, as shown in fig. 4, which is a schematic structural diagram of another launch vehicle telemetry system provided in the embodiment of the present application, as an implementable manner, on the basis of the above embodiments, the rocket-borne telemetry module 201 includes a first signal conversion device 2012, and the ground control module 202 includes a second signal conversion device 2021;
the second signal conversion device 2021 is configured to convert the control instruction in the digital signal form into a corresponding control instruction in the optical signal form, and send the control instruction in the optical signal form to the rocket-borne telemetry module 201; a first signal conversion device 2012, configured to convert the received control instruction in the form of the optical signal into a corresponding control instruction in the form of a digital signal; converting the detection data in the form of digital signals into corresponding detection data in the form of optical signals, and sending the detection data in the form of optical signals to the ground control module 202; the second signal conversion device 2021 is further configured to convert the detection data in the form of the received optical signal into corresponding detection data in the form of a digital signal.
Specifically, after receiving the control instruction and the detection data, the rocket-borne telemetry module 201 and the ground control module 202 both need to perform signal format conversion, that is, convert the optical signal transmitted by the optical fiber link 203 into a corresponding digital signal. Similarly, before sending the detection data and the control command, the rocket-borne telemetry module 201 and the ground control module 202 also need to perform signal format conversion, that is, convert the digital signal to be sent into a corresponding optical signal for transmission by the optical fiber link 203.
On the basis of the above embodiments, in order to further reduce the data transmission pressure when there are a plurality of types of detections required, as shown in fig. 5, a schematic structural diagram of another launch vehicle telemetry system provided in the embodiments of the present application is shown, as an implementable manner, on the basis of the above embodiments, in an embodiment, the rocket-mounted telemetry module 201 includes a self-detection device 2013;
the self-detection device 2013 is configured to obtain detection data, perform self-detection according to the detection data, generate a self-detection result, and send the self-detection result to the ground control module 202.
Specifically, the data acquisition device 2011 sends the acquired detection data to the self-detection device 2013 through detecting a data link inside the telemetry module, and the self-detection device 2013 performs corresponding detection on the carrier rocket according to the detection data and generates a self-detection result.
The data volume occupied by the self-detection result is usually smaller than the data volume occupied by the detection data for detection, and at this time, only the self-detection result needs to be sent to the ground control module 202, so that the data transmission pressure is further reduced, and the signal conversion pressure of the first signal conversion device 2012 and the second signal conversion device 2021 is relieved.
The detection data received by the ground control module 202 is the detection data after two signal conversions and transmission through the long-distance optical fiber link 203, and the detection data received by the self-detection device 2013 is the detection data after transmission through the short-distance data link inside the detection telemetry module, that is, the detection data acquired by the self-detection device 2013 has stronger timeliness and higher reliability than the detection data acquired by the ground control module 202, so that the accuracy of the self-detection result is improved.
On the basis of the above embodiments, in order to improve the control capability of the ground control module 202 on the launch vehicle, as shown in fig. 6, which is a schematic structural diagram of another launch vehicle telemetry system provided in the embodiments of the present application, as an implementable manner, on the basis of the above embodiments, in an embodiment, the launch vehicle telemetry module 201 further includes a parameter configuration device 2014;
the ground control module 202 is further configured to send a configuration parameter instruction to the rocket-borne telemetry module 201; and the parameter configuration device 2014 is used for adjusting the configuration parameters of the carrier rocket according to the configuration parameter instructions.
It should be explained that the configuration parameter instruction includes the parameter type of the configuration parameter to be adjusted and the adjustment sequence of each configuration parameter.
Specifically, in an embodiment, when the ground control module 202 determines that the vehicle has a fault according to the detection result generated by the ground control module and/or the self-detection result, and the fault can be repaired by adjusting the configuration parameters of the vehicle, in order to improve the fault repairing efficiency, the ground control module is further configured to: and adjusting the configuration parameter instruction according to the detection result and/or the self-detection result.
For example, if it is determined that a fault occurs in an execution structure of the launch vehicle according to the detection result and/or the self-detection result, but the fault does not affect the launch task and/or the flight task of the launch vehicle, the execution structure may be closed by adjusting configuration parameters corresponding to the execution structure, so that the execution structure does not participate in control during the flight and/or launch process.
Specifically, in one embodiment, for recyclable launch vehicles, the launch task status is diverse, the configuration parameters are adjusted more frequently, and for efficiency of adjustment of the configuration parameters, the ground control module 202 is further configured to: and acquiring a preset transmitting task requirement, and generating a configuration parameter instruction according to the preset transmitting task requirement.
The preset transmission task requirement comprises relevant information such as transmission time, transmission longitude, transmission latitude and transmission time.
Based on the above embodiments, in order to avoid the breakage of the optical fiber link 203 caused by the pulling of the optical fiber link 203 by the launch vehicle during the launch process, as shown in fig. 7, which is a schematic structural diagram of another remote measurement system for the launch vehicle provided in the embodiments of the present application, as an implementable manner, on the basis of the above embodiments, in an embodiment, the optical fiber link 203 is provided with a unplugging connector 2031.
The unplugging connector 2031 is configured to receive a unplugging signal sent by the ground control module 202 when the launch vehicle is to be launched, and perform separation processing according to the unplugging signal, so as to disconnect the optical fiber link 203.
It should be noted that the detachable connector 2031 is a plug-in connector based on a single-core plug and an adapter, and can be manually inserted and separated by an operator. In this embodiment, in order to improve the automation performance of the remote measurement system of the launch vehicle and save human resources, the unplugging connector 2031 comprises a control unit, and the control unit may control the unplugging connector 2031 to perform the detaching process according to the received unplugging signal.
For example, the unplugging connector 2031 is in a plugged-in state when power is supplied, and when the control unit receives a unplugging signal, the circuit in the unplugging connector 2031 can be controlled to be disconnected. After the circuit is broken, the unplugged connector 2031 will automatically disconnect, i.e., the fiber link 203 is disconnected.
On the basis of the above embodiment, because the temperature of the tail flame of the rocket is extremely high during the launching process of the rocket, after the launching task is finished, the optical fiber link 203 is seriously burnt, that is, after the launching task is finished each time, the optical fiber link 203 needs to be replaced, the replacement process is complicated, a large amount of human resources are consumed, and economic loss is caused.
In order to solve the above problem, as shown in fig. 8, a schematic structural diagram of another launch vehicle telemetry system provided in the embodiment of the present application is provided, as an implementable manner, on the basis of the above embodiment, in an embodiment, a fiber optic transition head 2032 is provided on a fiber optic link 203 between a unplugging connector 2031 and a ground control module 202; the fiber optic transition head 2032 is used for isolating the tail flame of the launch vehicle when the launch vehicle is launched.
It should be explained that the optical fiber conversion head 2032 is provided with a protection device and has a thermal insulation function, so that the tail flame of the launch vehicle, the flame on the burnt optical fiber link 203 and the high temperature can be effectively insulated.
Specifically, after the launch of the launch vehicle is completed, only one segment of the optical fiber link 203 between the unplugging connector 2031 and the optical fiber conversion head 2032 needs to be replaced, so that the replacement efficiency is improved, and meanwhile, the economic loss is reduced.
According to the structural schematic diagram of the conventional remote measuring system of the conventional launch vehicle shown in fig. 1, it can be determined that the RS-422 circuit and the repeater are seriously burnt during the launching process of the conventional remote measuring system of the launch vehicle, and the economic loss is serious. The remote measuring system of the carrier rocket provided by the embodiment of the application has the advantages that only a few parts of the optical fiber links 203 are burnt at each time, the manufacturing cost of the optical fiber links 203 is relatively low, and the launching cost of the carrier rocket is reduced.
The utility model provides a carrier rocket telemetering system that embodiment provided includes: the rocket-borne telemetry module and the ground control module; the rocket-borne telemetry module comprises a data acquisition device, and is connected with the ground control module through an optical fiber link; the ground control module is used for sending a control command to the rocket-borne telemetry module; the rocket-borne telemetry module is used for acquiring a control instruction, controlling the data acquisition device to acquire corresponding detection data according to the control instruction, and sending the detection data to the ground control module based on the optical fiber link; and the ground control module is also used for acquiring detection data, detecting the carrier rocket according to the detection data and generating a detection result. The system provided by the scheme can control the data acquisition device to acquire the currently required detection data through the control instruction, namely only the currently required detection data is transmitted at each time, so that the data transmission pressure is reduced, the data transmission efficiency is improved, the detection data in the system is transmitted based on the optical fiber link, the transmission speed is high, and the data transmission efficiency is further improved.
It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications therefrom are within the scope of the invention.
Claims (8)
1. A launch vehicle telemetry system, comprising: the rocket-borne telemetry module and the ground control module; the rocket-borne telemetry module comprises a data acquisition device, and is connected with the ground control module through an optical fiber link;
the ground control module is used for sending a control instruction to the rocket-borne telemetry module;
the rocket-borne telemetry module is used for acquiring the control instruction, controlling a data acquisition device to acquire corresponding detection data according to the control instruction, and sending the detection data to the ground control module based on the optical fiber link;
the ground control module is also used for acquiring the detection data, detecting the carrier rocket according to the detection data and generating a detection result;
wherein the on-board telemetry module comprises a self-detection device;
the self-detection device is used for acquiring the detection data, performing self-detection according to the detection data, generating a self-detection result and sending the self-detection result to the ground control module;
the ground control module is also used for acquiring a preset detection requirement and generating the control instruction according to the preset detection requirement; the preset detection requirement comprises a detection type and a detection time.
2. A launch vehicle telemetry system according to claim 1, wherein said rocket-borne telemetry module further includes parameter configuration means;
the ground control module is also used for sending a configuration parameter instruction to the rocket-borne telemetry module;
and the parameter configuration device is used for adjusting the configuration parameters of the carrier rocket according to the configuration parameter instruction.
3. The launch vehicle telemetry system of claim 2 wherein the ground control module is further configured to:
and adjusting the configuration parameter instruction according to the detection result and/or the self-detection result.
4. The launch vehicle telemetry system of claim 2 wherein the ground control module is further configured to:
and acquiring a preset launching task requirement, and generating the configuration parameter instruction according to the preset launching task requirement.
5. The launch vehicle telemetry system of claim 1 wherein the rocket-borne telemetry module and the ground control module each employ an ethernet communication protocol.
6. The launch vehicle telemetry system of claim 1 wherein a unplugged connector is provided on the fiber optic link;
and the unplugging connector is used for receiving a unplugging signal sent by the ground control module when the carrier rocket is to be launched, and performing separation processing according to the unplugging signal so as to disconnect the optical fiber link.
7. A launch vehicle telemetry system according to claim 6, characterised in that a fibre optic transition head is provided on the fibre optic link between the unplugging connector and the ground control module;
the optical fiber conversion head is used for isolating the tail flame of the carrier rocket during launch of the carrier rocket.
8. A launch vehicle telemetry system as claimed in claim 1, wherein said rocket-borne telemetry module includes first signal conversion means and said ground control module includes second signal conversion means;
the second signal conversion device is used for converting the control instruction in the form of a digital signal into a corresponding control instruction in the form of an optical signal and sending the control instruction in the form of the optical signal to the rocket-borne telemetry module;
the first signal conversion device is used for converting the control instruction in the form of the received optical signal into a control instruction in the form of a corresponding digital signal; converting the detection data in the form of digital signals into detection data in the form of corresponding optical signals, and sending the detection data in the form of the optical signals to the ground control module;
the second signal conversion device is further configured to convert the received detection data in the optical signal form into corresponding detection data in the digital signal form.
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| CN112968737B (en) * | 2021-02-04 | 2022-07-22 | 湖北航天技术研究院总体设计所 | System and method for self-closed loop test of carrier rocket wireless link and rocket |
| CN112994804B (en) * | 2021-05-13 | 2021-08-17 | 星河动力(北京)空间科技有限公司 | Rocket telemetry data processing method and device, electronic equipment and storage medium |
| CN114688926B (en) * | 2022-03-22 | 2024-06-04 | 中国运载火箭技术研究院 | Carrier rocket health detection verification evaluation system and method |
| CN117054136B (en) * | 2023-08-15 | 2024-06-11 | 东方空间技术(山东)有限公司 | Measurement system and method for recyclable carrier rocket |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US8888050B1 (en) * | 2011-02-15 | 2014-11-18 | Design—Net Engineering, LLC | Launch vehicle payload interface systems and methods |
| CN202841175U (en) * | 2012-08-17 | 2013-03-27 | 上海航天测控通信研究所 | Carrier rocket ground test, emission and control communication system |
| CN104597854B (en) * | 2013-10-30 | 2017-04-26 | 北京临近空间飞行器***工程研究所 | Automatic interpretation system and automatic interpretation method for telemetry data batch processing |
| CN206224222U (en) * | 2016-11-08 | 2017-06-06 | 北京航天万源科技有限公司 | A kind of carrier rocket emergency flight control equipment based on fiber optic communication |
| CN209446297U (en) * | 2019-01-30 | 2019-09-27 | 蓝箭航天空间科技股份有限公司 | The equivalent test device of Solid Launch Vehicle |
| CN109870070A (en) * | 2019-03-01 | 2019-06-11 | 北京星际荣耀空间科技有限公司 | A kind of integrated wireless launch vehicle measurement applied to Solid Launch Vehicle |
| CN110412910B (en) * | 2019-07-01 | 2020-12-18 | 中国航天空气动力技术研究院 | Aircraft wireless measurement and launch control system |
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2020
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