CN111405683A - Ground test launch control communication system of rocket - Google Patents
Ground test launch control communication system of rocket Download PDFInfo
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- CN111405683A CN111405683A CN202010207075.2A CN202010207075A CN111405683A CN 111405683 A CN111405683 A CN 111405683A CN 202010207075 A CN202010207075 A CN 202010207075A CN 111405683 A CN111405683 A CN 111405683A
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- transceiver module
- wireless transceiver
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- communication system
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04W—WIRELESS COMMUNICATION NETWORKS
- H04W76/00—Connection management
- H04W76/10—Connection setup
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B1/00—Details of transmission systems, not covered by a single one of groups H04B3/00 - H04B13/00; Details of transmission systems not characterised by the medium used for transmission
- H04B1/38—Transceivers, i.e. devices in which transmitter and receiver form a structural unit and in which at least one part is used for functions of transmitting and receiving
- H04B1/40—Circuits
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- Computer Networks & Wireless Communication (AREA)
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Abstract
The application provides a ground test, launch and control communication system of a rocket, which comprises a near-end communication subsystem and a far-end communication subsystem, wherein the near-end communication subsystem comprises a near-end wireless transceiver module, the far-end communication subsystem comprises a far-end wireless transceiver module, and the near-end wireless transceiver module is in communication connection with the far-end wireless transceiver module through a wireless network. This application utilizes wireless transceiver module to transmit multiple signal, has reduced cable laying and corollary equipment, the cost is reduced to simplify the ground and surveyed the equipment constitution who sends out accuse communication system, improved the system integration degree.
Description
Technical Field
The application relates to the field of aerospace, in particular to a ground test, launch and control communication system of a rocket.
Background
In the field of existing space rocket testing, a ground testing, launching and control system is divided into a far-end device and a near-end device, the distance between the front-end device and the rear-end device is several kilometers, and the front-end device and the rear-end device are connected through an optical cable, so that the purpose of remote control is achieved. The near-far end communication of the ground measurement and launch control system uses a traditional wired communication mode, such as well-known bus forms of RS422, RS485, 1553B, CAN, Ethernet and the like. The mainstream scheme is to use ethernet as a wired information transmission medium, and for long-distance transmission, convert an electrical signal into an optical signal and transmit the optical signal through an optical fiber. The wired transmission mode has high reliability and is successfully applied to a plurality of models.
However, the wired transmission method mainly has the following problems:
firstly, the cable product is often not known in the initial stage of development, in which launching field and launching station a rocket is to be launched, different launching fields and different launching stations have different requirements for cable lengths, and in order to adapt to various possible situations, the length of a cable network can only be considered according to the farthest distance, so that the cable network margin is often too large; for some inexperienced designers, it may even result in insufficient cable network length to be re-commissioned, affecting schedule and cost.
The length of the cable between the second ground and the near-far end is often in the kilometer level, the cable needs to be laid and protected in the preparation stage of the transmitting place, which often needs the time from half a day to one day, which not only generates the occupation cost of the transmitting place, but also obviously becomes a restriction factor for higher and higher quick transmitting requirements.
Thirdly, the glass wire core in the optical fiber is fragile, the wire core can be damaged or damaged if the optical fiber is subjected to excessive pressure, and hidden dangers can be caused if the optical fiber is treaded by people or pressed by heavy objects in the daily test use process, and the hidden dangers can be hidden and not known by the testing personnel, so that the reliable emission is adversely affected.
In recent years, with the increasing demand of rocket tests, the type of test information has not been limited to simple control and data commands, and video monitoring signals, voice control signals, wireless sensor signals are gradually added to the rocket tests. The signals have the common characteristics of large data volume, strong randomness and high real-time property. In the face of the requirement of simultaneous transmission of multiple signals, the traditional wired communication mode is difficult to meet the requirement of simultaneous transmission of multiple types of signals by means of single equipment.
One solution is to change the system architecture and add corresponding communication devices, which causes a significant cost burden. Moreover, the transmission distance of the common communication mode is generally short, and long-distance transmission can be realized only by adding optical fiber transmission equipment, so that not only are complicated procedures in arrangement and retraction brought, but also an intermediate transmission link is added, and a plurality of uncertain factors are brought.
Disclosure of Invention
An object of this application is to provide a ground survey is sent out and is controlled communication system, utilizes wireless transceiver module transmission multiple signal, the cost is reduced.
The application provides a ground test, launch and control communication system of a rocket, which comprises a near-end communication subsystem and a far-end communication subsystem, wherein the near-end communication subsystem comprises a near-end wireless transceiver module, the far-end communication subsystem comprises a far-end wireless transceiver module, and the near-end wireless transceiver module is in communication connection with the far-end wireless transceiver module through a wireless network.
Preferably, the antennas of the far-end wireless transceiver module and/or the near-end wireless transceiver module are redundant antennas, and the redundant antennas include a main antenna and a backup antenna.
Wherein, preferably, the main antenna is a directional antenna, and the effective communication distance of the directional antenna is not less than 2 km.
Wherein, the backup antenna is preferably an omnidirectional receiving antenna.
Preferably, the communication frequency of the far-end wireless transceiver module and/or the near-end wireless transceiver module is 1.2GHz-1.5GHz, and the communication rate is not lower than 5 Mbps.
Preferably, the far-end wireless transceiver module and/or the near-end wireless transceiver module use a single-carrier frequency domain equalization waveform as the physical transmission waveform.
Wherein, the receiver of the far-end wireless transceiver module and/or the near-end wireless transceiver module adopts the channel tracking based on the recursive least square method.
Wherein, preferably, under the condition that the communication distance is not less than 2km, the receiving margin of the far-end wireless transceiver module and/or the near-end wireless transceiver module is greater than 30 dB.
Preferably, the far-end wireless transceiver module and/or the near-end wireless transceiver module implement bidirectional and multipoint transmission in a time division duplex manner.
Preferably, the far-end wireless transceiver module and/or the near-end wireless transceiver module are/is provided with TT L level serial ports, RS232, RS422, Ethernet, SDI and Micro HDMI interfaces.
The beneficial effect of this application is as follows:
1. this application utilizes wireless transceiver module to transmit multiple signal, has reduced cable laying and corollary equipment, the cost is reduced to simplify the ground and surveyed the equipment constitution who sends out accuse communication system, improved the system integration degree.
2. This application has set up wireless transceiver module, and the antenna arrangement is nimble, can realize many signals simultaneous transmission in the effective communication range of kilometer, effectively reduces the dependence to the environment is laid to the launching field cable, improves the adaptability of launching field.
3. The wireless communication system is simple in composition and structure, the equipment can be applied after being electrified, the unfolding and folding speeds of the equipment are greatly improved, the rapidity of transmitting preparation is further improved, and the wireless communication system has a good engineering practical application prospect.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments described in the present application, and other drawings can be obtained by those skilled in the art according to the drawings.
Fig. 1 is a schematic structural diagram of a ground test, launch and control communication system of a rocket according to an embodiment of the present application.
Detailed Description
The technical solutions in the embodiments of the present application are 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, but not all, embodiments of the present application. 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.
Fig. 1 is a schematic structural diagram of a ground test, launch and control communication system of a rocket according to an embodiment of the present application. As shown in fig. 1, the ground test, launch and control communication system of the rocket comprises a near-end communication subsystem and a far-end communication subsystem. The near-end communication subsystem comprises a near-end wireless transceiving module, a high-definition camera, comprehensive control equipment, ground power supply and other testing equipment. The remote communication subsystem comprises a remote wireless transceiving module, a monitoring computer, a remote measuring terminal, a display control terminal and other testing equipment. The near-end wireless transceiver module is in communication connection with the far-end wireless transceiver module through a wireless network.
As an embodiment, as shown in FIG. 1, the near-end wireless transceiver module communicates with testing equipment such as a high-definition camera, an integrated control device and a ground power supply through the Ethernet to transmit information such as data and video, and the far-end wireless transceiver module communicates with testing equipment such as a monitoring computer, a remote measuring terminal and a display control terminal through the Ethernet to transmit data and video information.
As an embodiment, the near-end wireless transceiver module and the far-end wireless transceiver module have the same hardware design, and can be set as the near-end wireless transceiver module or the far-end wireless transceiver module in a software manner, and can provide wireless bidirectional data link between the near-end and the far-end by matching with the near-end antenna or the far-end antenna.
The near-end wireless transceiver module and the far-end wireless transceiver module are standard IP communication links, can perform networking, relay transmission and other functions, and support functions of multi-machine relay, air networking, multi-ground-station networking and the like. The near-end wireless transceiver module and the far-end wireless transceiver module respectively comprise two transceiving links, the two links respectively comprise a power amplifier circuit, a low-noise amplifier circuit and a transceiving switch, and the near-end wireless transceiver module and the far-end wireless transceiver module can be selected differently in appearance and devices according to the assembling position and the transmitting power of the test equipment.
In the process of transmitting multi-type signals, the near-end wireless transceiver module and/or the far-end wireless transceiver module realize bidirectional and multipoint transmission by adopting a Time Division Duplex (TDD) mode, so that the frequency occupation during networking is reduced, and the design of the whole system is simpler and more convenient.
The antenna of the wireless transceiver module is sensitive to the installation environment, and in order to improve the ability of the wireless signal to pass through the obstacle and improve the reliability of information transmission, preferably, the near-end wireless transceiver module and/or the far-end wireless transceiver module adopt a redundant antenna design, and the redundant antenna comprises a main antenna and a backup antenna. During installation, the main antenna and the backup antenna are fixed on the tripod through the threaded holes at the bottom, and the antenna is elevated by utilizing the tripod so as to eliminate ground interference.
In order to further increase the antenna gain, the main antenna is a directional antenna, the directional antenna adopts a micro-strip oscillator plate-shaped antenna with certain directivity, and the effective communication distance is not less than 2 km. The directional antenna can only transmit and receive signals in one direction, which is beneficial to the power concentration of the signals. Preferably, the main antenna adopts a glass fiber reinforced plastic directional antenna, and the glass fiber reinforced plastic directional antenna has strong wind resistance, long service life and long signal transmission distance and is suitable for outdoor use.
The backup antenna is an omnidirectional receiving antenna, does not send signals, and only receives normal communication instructions and emergency control signals, so that the communication system enhances the signal receiving capability and improves a wireless communication link.
The backup antenna can adopt a common rod-shaped plastic omnidirectional antenna. Preferably, in order to increase the receiving gain, the backup antenna adopts a glass fiber reinforced plastic omnidirectional antenna. Further, the ground omni-directional antenna gain is designed to be 6-8dBi, preferably 7 dBi.
The wireless network comprises a near-end wireless transceiver module and a far-end wireless transceiver module, wherein the near-end wireless transceiver module and/or the far-end wireless transceiver module are/is connected with the near-end wireless transceiver module and/or the far-end wireless transceiver module through a wireless network, the near-end wireless transceiver module and/or the far-end wireless transceiver module adopt a Single Carrier Frequency Domain Equalization (SCFDE) waveform as a physical transmission waveform, the waveform is an uplink waveform of 4G/L TE, and is suitable for being applied in an anti-interference and low-power-consumption environment.
In addition, in order to adapt to channel time variation caused by relative motion, the receiver adopts channel tracking based on a recursive least square method (R L S) to support a motion environment with a certain speed, and the fastest motion speed is more than 800 km/h.
In the rocket test, the wireless communication data stream mainly comprises a communication control stream, a test parameter data stream, a measurement parameter data stream, a high-definition video data stream and the like. In the actual wireless communication transmission process, besides the slow fading closely related to the distance and the occlusion, there is also time-varying fast fading, which causes the receiving level to fluctuate continuously. In order to avoid the packet loss phenomenon, preferably, under the condition that the effective communication distance is not less than 2km, the receiving margin of the far-end wireless transceiver module and/or the near-end wireless transceiver module is greater than 30dB, so that the near-end communication subsystem and the far-end communication subsystem can both communicate normally.
The near-end wireless transceiver module and the far-end wireless transceiver module can be used for setting parameters in a webpage access mode, and considering factors such as national policies and frequency interference, the wireless transceiver module preferably adopts L waveband with relatively high frequency band, the communication frequency is 1.2GHz-1.5GHz, the frequency is not prone to interference, high reliability and low error rate of communication are ensured, more preferably, the communication frequency is 1.4GHz, and the communication rate is not lower than 5Mbps so as to meet the requirement of transmission bandwidth.
The beneficial effect of this application is as follows:
1. this application utilizes wireless transceiver module to transmit multiple signal, has reduced cable laying and corollary equipment, the cost is reduced to simplify the ground and surveyed the equipment constitution who sends out accuse communication system, improved the system integration degree.
2. This application has set up wireless transceiver module, and the antenna arrangement is nimble, can realize many signals simultaneous transmission in the effective communication range of kilometer, effectively reduces the dependence to the environment is laid to the launching field cable, improves the adaptability of launching field.
3. The wireless communication system is simple in composition and structure, the equipment can be applied after being electrified, the unfolding and folding speeds of the equipment are greatly improved, the rapidity of transmitting preparation is further improved, and the wireless communication system has a good engineering practical application prospect.
While the preferred embodiments of the present application have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. Therefore, it is intended that the appended claims be interpreted as including preferred embodiments and all alterations and modifications as fall within the scope of the application. It will be apparent to those skilled in the art that various changes and modifications may be made in the present application without departing from the spirit and scope of the application. Thus, if such modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is intended to include such modifications and variations as well.
Claims (10)
1. The ground test, launch and control communication system of the rocket is characterized by comprising a near-end communication subsystem and a far-end communication subsystem, wherein the near-end communication subsystem comprises a near-end wireless transceiver module, the far-end communication subsystem comprises a far-end wireless transceiver module, and the near-end wireless transceiver module is in communication connection with the far-end wireless transceiver module through a wireless network.
2. The ground test, transmission and control communication system according to claim 1, wherein the antennas of the far-end wireless transceiver module and/or the near-end wireless transceiver module are redundant antennas, and the redundant antennas include a main antenna and a backup antenna.
3. The ground test, launch and control communication system of claim 2 wherein the primary antenna is a directional antenna having an effective communication distance of no less than 2 km.
4. A ground based transmission and control communication system according to claim 2 or 3 wherein the backup antenna is an omni-directional receive antenna.
5. The ground test, launch and control communication system according to claim 1, wherein the communication frequency of the far-end wireless transceiver module and/or the near-end wireless transceiver module is 1.2GHz-1.5GHz, and the communication rate is not lower than 5 Mbps.
6. The ground test, transmission and control communication system according to claim 1, wherein the far-end wireless transceiver module and/or the near-end wireless transceiver module employ a single carrier frequency domain equalization waveform as a physical transmission waveform.
7. The ground test, transmission and control communication system according to claim 1, wherein the receiver of the far-end wtru and/or the near-end wtru employs channel tracking based on recursive least squares.
8. The ground test, transmission and control communication system according to claim 1, wherein a reception margin of the far-end wireless transceiver module and/or the near-end wireless transceiver module is greater than 30dB under a condition that a communication distance is not less than 2 km.
9. The ground test, transmission and control communication system according to claim 1, wherein the far-end wtru and/or the near-end wtru performs bi-directional and multi-point transmission using tdd.
10. The ground test, launch and control communication system according to claim 1, wherein the remote wireless transceiver module and/or the near wireless transceiver module has TT L level serial port, RS232, RS422, ethernet, SDI, Micro HDMI interface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010207075.2A CN111405683A (en) | 2020-03-23 | 2020-03-23 | Ground test launch control communication system of rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010207075.2A CN111405683A (en) | 2020-03-23 | 2020-03-23 | Ground test launch control communication system of rocket |
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| CN111405683A true CN111405683A (en) | 2020-07-10 |
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| CN202010207075.2A Pending CN111405683A (en) | 2020-03-23 | 2020-03-23 | Ground test launch control communication system of rocket |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104764479A (en) * | 2015-03-05 | 2015-07-08 | 上海微小卫星工程中心 | Satellite wireless test system based on Zigbee |
| US9742058B1 (en) * | 2015-08-06 | 2017-08-22 | Gregory A. O'Neill, Jr. | Deployable quadrifilar helical antenna |
| CN110233705A (en) * | 2019-06-11 | 2019-09-13 | 北京深蓝航天科技有限公司 | Signal transmission system based on communication |
-
2020
- 2020-03-23 CN CN202010207075.2A patent/CN111405683A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104764479A (en) * | 2015-03-05 | 2015-07-08 | 上海微小卫星工程中心 | Satellite wireless test system based on Zigbee |
| US9742058B1 (en) * | 2015-08-06 | 2017-08-22 | Gregory A. O'Neill, Jr. | Deployable quadrifilar helical antenna |
| CN110233705A (en) * | 2019-06-11 | 2019-09-13 | 北京深蓝航天科技有限公司 | Signal transmission system based on communication |
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Application publication date: 20200710 |
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