CN101030803A - Satellite-carried wireless data transmitter - Google Patents
Satellite-carried wireless data transmitter Download PDFInfo
- Publication number
- CN101030803A CN101030803A CN 200610109944 CN200610109944A CN101030803A CN 101030803 A CN101030803 A CN 101030803A CN 200610109944 CN200610109944 CN 200610109944 CN 200610109944 A CN200610109944 A CN 200610109944A CN 101030803 A CN101030803 A CN 101030803A
- Authority
- CN
- China
- Prior art keywords
- intermediate frequency
- circuit
- satellite
- output
- isolator
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Landscapes
- Transmitters (AREA)
Abstract
本发明公开了一种星载无线数据传输发射机，包括一射频电路、一基带信号处理电路；一中频调制电路与所述基带信号处理电路连接；一中频晶振电路与所述中频调制电路连接；所述射频电路与所述中频调制电路连接。一电源电路，分别与所述基带信号处理电路、所述中频调制电路、所述本振电路、所述射频电路连接。本发明的优点在于减小了发射机的旁瓣发射、整机体积小、重量轻、通信距离远、抗辐照、剩磁小。
The invention discloses a satellite-borne wireless data transmission transmitter, which comprises a radio frequency circuit and a baseband signal processing circuit; an intermediate frequency modulation circuit is connected with the baseband signal processing circuit; an intermediate frequency crystal oscillator circuit is connected with the intermediate frequency modulation circuit; The radio frequency circuit is connected with the intermediate frequency modulation circuit. A power supply circuit, respectively connected to the baseband signal processing circuit, the intermediate frequency modulation circuit, the local oscillator circuit, and the radio frequency circuit. The invention has the advantages of reduced side lobe emission of the transmitter, small volume, light weight, long communication distance, anti-irradiation and small residual magnetism.
Description
Technical field
The present invention relates to wireless data transmitter, particularly a kind of satellite-carried wireless data transmitter.
Background technology
" double star " survey plan that is proposed by Chinese Space physicist Liu Zhenxing academician 1997 is to utilize 2 satellites that near-earth equatorial region and the electromagnetic field of these two main magnetosphere behaviour areas, polar region and the change in time and space of energy particle are carried out combined detection.The double star plan matches with the Cluster survey plan of European Space Agency, obtains very valuable results.The double star plan will be to surveying from unexplored area of space on the human history, a satellite is around dry running on the South Pole and the arctic, another is around equator operation, utilizes 2 satellites that near-earth equatorial region and the electromagnetic field of these two main magnetosphere behaviour areas, polar region and the change in time and space of energy particle are carried out combined detection.
When satellite during through the visual segmental arc of grounded receiving station, payload is surveyed on the star science data and engineering telemetry parameter can be beamed back ground by wireless data transmitter and antenna system thereof.
Existing transmitter, its sidelobe emission is bigger, can cause interference to the answering machine on the satellite, and not at the space environment of satellite transit, transmitter is carried out anti-irradiation, remanent magnetism, thermal design, structural design etc.
Therefore, just need that a kind of sidelobe emission is little, machine volume is little, in light weight, communication distance is far away, anti-irradiation, satellite-carried wireless data transmitter that remanent magnetism is little.
Summary of the invention
The objective of the invention is to overcome the deficiencies in the prior art, provide that a kind of sidelobe emission is little, machine volume is little, in light weight, communication distance is far away, anti-irradiation, satellite-carried wireless data transmitter that remanent magnetism is little.
In order to achieve the above object, the technical scheme taked of the present invention comprises:
A kind of satellite-carried wireless data transmitter comprises:
One base band signal process circuit;
One modulation circuit of intermediate frequency, this modulation circuit of intermediate frequency receives the input signal of described base band signal process circuit;
One intermediate frequency crystal oscillating circuit (7) is connected with described modulation circuit of intermediate frequency;
One radio circuit is connected with described modulation circuit of intermediate frequency.
In technique scheme, further, also comprise a power circuit, be connected with described base band signal process circuit, described modulation circuit of intermediate frequency, described local oscillation circuit, described radio circuit respectively.
In technique scheme, further, described base band signal process circuit is an encoder, and this encoder receives the clock signal and the digital signal of data management system input on the star.
In technique scheme, further, described modulation circuit of intermediate frequency is linked in sequence by an intermediate frequency modulator, an intermediate-frequency filter, an intermediate frequency amplifier, a upconverter and one second isolator and forms; The output of described encoder inserts described intermediate frequency modulator, and described intermediate frequency modulator output connects intermediate-frequency filter, and described intermediate-frequency filter output connects intermediate frequency amplifier, and this intermediate frequency amplifier output connects frequency converter, and this upconverter is connected to second isolator.
In technique scheme, further, described intermediate frequency crystal oscillating circuit (7) comprising: an intermediate frequency crystal oscillating circuit (7) output two paths of signals, and wherein one road signal connects an amplifier, and this amplifier output connects described intermediate frequency modulator; Another road signal output connects a local oscillation circuit; This local oscillation circuit output connects first isolator, and this first isolator output connects described upconverter.
In technique scheme, further, described radio circuit comprises: a up-converting filter, this up-converting filter output connects one the 3rd isolator, the output of the 3rd isolator connects a radio-frequency power amplifier, this radio-frequency power amplifier output connects one the 4th isolator, and the output of the 4th isolator connects a transmitting filter; Described second isolator output connects described up-converting filter.
In technique scheme, further, described power circuit is a DC/DC power supply, and this power supply is the inner power supply that uses of transmitter with the power conversion that satellite system offers transmitter.
Compared with prior art, the invention has the advantages that:
1) transmitter of the present invention has all inserted filter at intermediate frequency node, up-conversion node and radio frequency output node, thereby has reduced the sidelobe emission of transmitter, avoids the answering machine on the satellite is caused interference.
2) machine volume is little, in light weight, communication distance is far away, anti-irradiation, remanent magnetism are little.
Description of drawings
Fig. 1 is a wireless data transmitter theory diagram of the present invention.
The drawing explanation:
1-encoder 2-intermediate frequency modulator
3-intermediate-frequency filter 4-intermediate frequency amplifier
5-upconverter 6-second isolator
7-crystal oscillator 8-amplifier
9-local oscillator 10-first isolator
11-up-converting filter 12-the 3rd isolator
13-radio-frequency power amplifier 14-the 4th isolator
15-transmitting filter 16-DC/DC power supply
Embodiment
Below in conjunction with the drawings and specific embodiments the present invention is described in further detail:
With reference to Fig. 1, make transmitter of the present invention, the serial data stream of input is separated into homophase and quadrature two-way dibit code stream in encoder 1, and then carries out differential coding.Transmitter crystal oscillator 7 one tunnel is supplied with intermediate frequency modulator 2 and is used as modulation after amplifying; Local oscillator 9 is supplied with as a reference in another road behind frequency division.The output of intermediate frequency modulator 2 is sent into upconverter 5 and local oscillation signal mixing then through the out of band spectrum of intermediate-frequency filter 3 in order to the restriction phase-modulated signal behind intermediate frequency amplifier 4.Can obtain the upper side band signal of 2287.5MHz after the upconverter mixing, up-conversion filter 11 is in order to filtering local oscillator and lower sideband signal etc.Transmitting filter 15 is in order to further filtering out of band spectrum.Compare with similar transmitter, this transmitter has all inserted filter at intermediate frequency node, up-conversion node and radio frequency output node, thereby has reduced the sidelobe emission of transmitter, can not cause interference to the answering machine on the satellite.
Specifically, each parts in the transmitter are respectively:
Local oscillator 9 is made of the phase locking frequency multiplying source, produces 2217.5MHZ local oscillation signal source;
Radio-frequency power amplifier 13 produces the output of 14W power by power amplifier;
Transmitting filter 15 bandwidth are the band pass filter of 9MHZ, and stopband suppresses greater than 60dB;
Forward loss≤the 0.5dB of isolator 6,10,12,14, reverse loss 〉=20dB.
DC/DC power supply 16, the power conversion that this power supply offers transmitter with satellite system are the inner power supply that uses of transmitter, be transformed in the present embodiment+10V ,+5V and-three kinds of power supplys of 5V.
The overall emission machine structurally is divided into three layers, compact in design, and each layer all shields isolation to each element circuit, strengthens the integrated level and the Electro Magnetic Compatibility of transmitter circuitry, makes that volume reduces, weight saving.
In order to adapt to the space environment of satellite transit, transmitter is carried out anti-irradiation, remanent magnetism, thermal design, structural design etc.The mode of taking is as follows:
1. anti-irradiation design
The object that the anti-irradiation of S-band transmitter is reinforced mainly is a digital circuit, designs according to the anti-irradiation ability of device.Cmos device in the coding circuit is changed to the TTL device.After the irradiation test result showed employing TTL device, the anti-irradiation ability of circuit obviously improved.
2. magnetic design
When structural design, transmitter internal insulation device is oppositely placed in twos, promptly realized the transmitter internal compensation.Remanent magnetism is not 1023mAm before the compensation
2, reduce to 196mAm after the compensation
2This result still can not meet the demands, and still need further compensate, and places an opposite polarity 200mAm in transmitter complete machine Z direction
2Magnetic patch, remanent magnetism is reduced to 47mAm
2The Z direction is meant herein: during the transmitter horizontal positioned, perpendicular to the direction of horizontal plane.
Transmitter of the present invention has reduced the sidelobe emission of transmitter, avoid the answering machine on the satellite is caused interference, and machine volume is little, in light weight, communication distance is far away, and communication distance is greater than 80,000 kilometers.
It should be noted last that above embodiment is only unrestricted in order to technical scheme of the present invention to be described.Although the present invention is had been described in detail with reference to embodiment, those of ordinary skill in the art is to be understood that, technical scheme of the present invention is made amendment or is equal to replacement, do not break away from the spirit and scope of technical solution of the present invention, it all should be encompassed in the middle of the claim scope of the present invention.
Claims (8)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200610109944 CN101030803A (en) | 2006-02-27 | 2006-08-25 | Satellite-carried wireless data transmitter |
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200610008195.X | 2006-02-27 | ||
| CN200610008195 | 2006-02-27 | ||
| CN 200610109944 CN101030803A (en) | 2006-02-27 | 2006-08-25 | Satellite-carried wireless data transmitter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101030803A true CN101030803A (en) | 2007-09-05 |
Family
ID=38715916
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200610109944 Pending CN101030803A (en) | 2006-02-27 | 2006-08-25 | Satellite-carried wireless data transmitter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101030803A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103220043A (en) * | 2013-03-27 | 2013-07-24 | 广州飞瑞敖电子科技有限公司 | Combiner or shunt way of double-line WiFi signal mixed transmission |
| CN103312453A (en) * | 2013-03-12 | 2013-09-18 | 中国电子科技集团公司第十研究所 | Self-adaptive distance data transmission method for aircraft-mounted terminal |
| CN105099537A (en) * | 2014-05-08 | 2015-11-25 | 中国科学院空间科学与应用研究中心 | Digital transmission sender used for satellite |
| CN107483099A (en) * | 2017-08-30 | 2017-12-15 | 长光卫星技术有限公司 | Spaceborne Equipment Isolation and Security System |
| CN113890590A (en) * | 2021-10-12 | 2022-01-04 | 北京微纳星空科技有限公司 | A satellite-borne data transmission device, system and intelligent terminal |
-
2006
- 2006-08-25 CN CN 200610109944 patent/CN101030803A/en active Pending
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103312453A (en) * | 2013-03-12 | 2013-09-18 | 中国电子科技集团公司第十研究所 | Self-adaptive distance data transmission method for aircraft-mounted terminal |
| CN103312453B (en) * | 2013-03-12 | 2016-07-06 | 中国电子科技集团公司第十研究所 | The method that aircraft mounted terminal self adaptation distance number passes |
| CN103220043A (en) * | 2013-03-27 | 2013-07-24 | 广州飞瑞敖电子科技有限公司 | Combiner or shunt way of double-line WiFi signal mixed transmission |
| CN103220043B (en) * | 2013-03-27 | 2015-08-26 | 广州飞瑞敖电子科技有限公司 | Conjunction road/shunt the mode of two-way WiFi signal mixed transport |
| CN105099537A (en) * | 2014-05-08 | 2015-11-25 | 中国科学院空间科学与应用研究中心 | Digital transmission sender used for satellite |
| CN107483099A (en) * | 2017-08-30 | 2017-12-15 | 长光卫星技术有限公司 | Spaceborne Equipment Isolation and Security System |
| CN107483099B (en) * | 2017-08-30 | 2020-09-01 | 长光卫星技术有限公司 | Spaceborne equipment isolation and security system |
| CN113890590A (en) * | 2021-10-12 | 2022-01-04 | 北京微纳星空科技有限公司 | A satellite-borne data transmission device, system and intelligent terminal |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101030803A (en) | Satellite-carried wireless data transmitter | |
| CN112566195B (en) | Information transmission method, device and system | |
| CN106712833B (en) | Aircraft integrated information processing subsystem and aerospace measurement and control system | |
| CN103412288B (en) | All solid state X-band portable radar Radio Beacon and signal processing method thereof | |
| ATE519284T1 (en) | CELLULAR RADIO TELEPHONE DEVICE FOR USE ON BOARD A VEHICLE | |
| CN101048942A (en) | Transmit-receive switch architecture providing pre-transmit isolation | |
| CN112584451A (en) | Neighbor relation configuration method and device suitable for satellite network | |
| CN102761352A (en) | FDD-LTE (Frequency Division Duplexing-Long Term Evolution) indoor coverage system and signal transmission method | |
| Pugh et al. | The universal space transponder: A next generation software defined radio | |
| CN101521962B (en) | System for generating single side band high-frequency optical fiber millimeter wave and reusing wavelength | |
| CN101674111B (en) | Communication system for mobile devices in the air | |
| CN104301058A (en) | Multi-code-rate multi-channel multi-system measurement and control system of microsatellite | |
| Zeedan et al. | Cubesat communication subsystems: A review of on-board transceiver architectures, protocols, and performance | |
| CN103888183B (en) | A kind of method that round-the-clock communication is realized using two IGSO telecommunication satellites | |
| CN105099537A (en) | Digital transmission sender used for satellite | |
| CN112448753B (en) | Communication method and device | |
| CN200953554Y (en) | A S-Band Data Transmission Transmitter Suitable for Space Applications | |
| CN115801036A (en) | 5G millimeter wave bidirectional double-frequency transceiver mechanism | |
| CN109361052A (en) | A chip dual-frequency airborne satellite communication antenna | |
| CN203324472U (en) | All-solid-state X-wave-band portable radar beacon machine | |
| CN2831265Y (en) | Microwave module of roadside unit in electronic non-parking charging short-range communication system | |
| CN103067326A (en) | Telemetering and data transmission integrated transmitter | |
| CN111181622B (en) | Configurable digital multimedia broadcasting micro wireless repeater | |
| CN200983589Y (en) | Bidirectional conversion integrated circuit between RF signals and middle-frequency wired signals | |
| CN212540723U (en) | Wireless filling system for underwater Beidou navigation ephemeris and almanac |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |