CN102684773A - Method for designing high-speed data transmission interfaces of polar-orbit meteorological satellites - Google Patents
Method for designing high-speed data transmission interfaces of polar-orbit meteorological satellites Download PDFInfo
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- CN102684773A CN102684773A CN2012101190964A CN201210119096A CN102684773A CN 102684773 A CN102684773 A CN 102684773A CN 2012101190964 A CN2012101190964 A CN 2012101190964A CN 201210119096 A CN201210119096 A CN 201210119096A CN 102684773 A CN102684773 A CN 102684773A
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Abstract
The invention provides a method for designing high-speed data transmission interfaces of polar-orbit meteorological satellites, which is implemented based on an RS-422 interface circuit form, and comprises the following steps that: a sending-end interface chip 26C31 is provided, and the positive and negative signal ends of the sending-end interface chip 26C31 are respectively connected in series with a resistor R1; and a receiving-end interface chip 26C32 is provided, the positive power supply end of the receiving-end interface chip 26C32 is connected in series with a diode D, a resistor R2 is connected in series between the diode D and the positive signal end of the receiving-end interface chip 26C32, a negative power supply end of the receiving-end interface chip 26C32 is connected in series with a resistor R4, and a resistor R3 is connected in series between the positive and negative signal ends of the receiving-end interface chip 26C32. According to the design method provided by the invention, the design problem of multi-load and unbalanced code rate data transmission interfaces of polar-orbit meteorological satellites is solved conveniently and reliably.
Description
Technical field
The present invention relates to a kind of Design of Interface Circuit method, in particular, relate to a kind of method for designing of polar orbiting meteorological satellite high speed data transmission interface.
Background technology
China a new generation polar orbiting meteorological satellite is China's second generation polar orbiting meteorological satellite, is used for realizing global, round-the-clock, three-dimensional, quantitative remote sensing.The difficult point that its number passes system design is to accomplish the information processing of multi-load, different bit rates.
Along with the raising of meteorological satellite sounding business demand, in the future satellite will carry the load that multipotency is more enough accomplished different detection missions; In addition, along with the development of load technology, load is surveyed and will be realized more high-resolution, more frequency range covering, more highly sensitive technology surveyed more.Logarithm biography system will bring more load datas, more big data quantity, higher bit rate data processing reach the design requirement that passes down.
Summary of the invention
The present invention is directed to the technical problem that exists in the above-mentioned prior art, a kind of polar orbiting meteorological satellite high speed data transmission interface method for designing is provided, realized the problem that polar orbiting meteorological satellite multi-load, unbalanced bit rate data transmission interface design easily and reliably.
For achieving the above object, the technical scheme that the present invention adopted is following:
A kind of method for designing of polar orbiting meteorological satellite high speed data transmission interface circuit based on RS-422 interface circuit form, comprises in this design circuit:
Transmitting terminal interface chip 26C31 is used for the transmission of data and clock signal; Difference series resistor R1 is used to protect transmitting terminal interface chip 26C31 on the signal positive and negative terminal of transmitting terminal interface chip 26C31;
Receiving terminal interface chip 26C32 is used for the reception of data and clock signal; Power supply anode serial connection diode D at receiving terminal interface chip 26C32 is used to protect receiving terminal interface chip 26C32; Series resistor R2 between the signal anode of diode D and receiving terminal interface chip 26C32; Power supply negative terminal series resistor R4 at receiving terminal interface chip 26C32; Series resistor R3 between the signal positive and negative terminal of receiving terminal interface chip 26C32, said resistance R 2, R3, R4 are used to control the drive current of receiving terminal interface chip 26C32.
Said transmitting terminal and receiving terminal are interface type of attachment one to one, that is, riches all the way exports after sending end interface chip 26C31 to connect one road receiving terminal interface chip 26C32.
Said transmitting terminal and receiving terminal are for intersecting the backup interface type of attachment, that is, two-way transmitting terminal interface chip 26C31 all connects one road receiving terminal interface chip 26C32 separately, this two-way receiving terminal interface chip 26C32 with then export as one road signal.
Said transmitting terminal and receiving terminal are a pair of two interface types of attachment, that is, riches all the way exports as two paths of signals after sending end interface chip 26C31 to connect two-way receiving terminal interface chip 26C32.
Said transmitting terminal and receiving terminal are two pairs one interface types of attachment, that is, two-way transmitting terminal interface chip 26C31 exports as one road signal after connecting one road receiving terminal interface chip 26C32.
The method for designing of the disclosed a kind of satellite high speed data transmission interface realized based on the RS-422 interface circuit of technical scheme of the present invention; Adopt transmitting terminal interface chip 26C31, the receiving terminal interface chip 26C32 of data and clock signal, and be serially connected in the transmission that protective circuit on transmitting terminal and the receiving terminal interface chip realizes data respectively.And four kinds of different interface chip types of service are provided, can have selected the interface shape of transmission, realized the problem that polar orbiting meteorological satellite multi-load, unbalanced bit rate data transmission interface design easily and reliably according to different needs.
Description of drawings
Fig. 1 is the type of attachment of interface one to one of the present invention;
Fig. 2 is an intersection backup interface type of attachment of the present invention;
Fig. 3 is a pair of two interface types of attachment of the present invention;
Fig. 4 is two pairs one interface types of attachment of the present invention.
Embodiment
Elaborate in the face of embodiments of the invention down: present embodiment provided detailed execution mode and concrete operating process, but protection scope of the present invention is not limited to following embodiment being to implement under the prerequisite with technical scheme of the present invention.
Like Fig. 1～shown in Figure 4, the method for designing of the disclosed polar orbiting meteorological satellite high speed data transmission interface of the present invention circuit is based on RS-422 interface circuit form, comprises in this design circuit:
Transmitting terminal interface chip 26C31 is used for the transmission of data and clock signal; Difference series resistor R1 is used to protect transmitting terminal interface chip 26C31 on the signal positive and negative terminal of transmitting terminal interface chip 26C31;
Receiving terminal interface chip 26C32 is used for the reception of data and clock signal; 5V power supply power supply anode serial connection diode D at receiving terminal interface chip 26C32 is used to protect receiving terminal interface chip 26C32; Series resistor R2 between the signal anode of diode D and receiving terminal interface chip 26C32; At the 5V of receiving terminal interface chip 26C32 power supply negative terminal series resistor R4; Series resistor R3 between the signal positive and negative terminal of receiving terminal interface chip 26C32; These three resistance R 2, R3, R4 are the drive currents that are used to control receiving terminal interface chip 26C32; Its resistance value can design according to the needs of side circuit, is used for regulating the size of the drive current of receiving terminal interface chip 26C32 through the size of adjustment resistance value.
As shown in Figure 1, transmitting terminal interface chip 26C31 and receiving terminal interface chip 26C32 are interface type of attachment one to one, that is, riches all the way send end interface chip 26C31 to connect that signal is one tunnel output behind one road receiving terminal interface chip 26C32.
As shown in Figure 2; Transmitting terminal interface chip 26C31 and receiving terminal interface chip 26C32 are for intersecting the backup interface type of attachment; Promptly; Two-way transmitting terminal interface chip 26C31 all connects one road receiving terminal interface chip 26C32 separately, and this two-way receiving terminal interface chip 26C32 exports as one road signal with the back.
As shown in Figure 3, transmitting terminal interface chip 26C31 and receiving terminal interface chip 26C32 are a pair of two interface types of attachment, that is, riches all the way exports as two paths of signals after sending end interface chip 26C31 to connect two-way receiving terminal interface chip 26C32.
As shown in Figure 4, said transmitting terminal interface chip 26C31 and receiving terminal interface chip 26C32 are two pairs one interface types of attachment, that is, two-way transmitting terminal interface chip 26C31 exports as one road signal after being connected to one road receiving terminal interface chip 26C32.
Obviously, those skilled in the art can not break away from the spirit and scope of the present invention to the satellite high speed data transmission interface of the present invention various changes of design carrying out and distortion.Like this, if these modifications and distortion belong within the scope of claim of the present invention and equivalent technologies thereof, then the present invention also is intended to comprise these changes and is out of shape interior.
Claims (5)
1. the method for designing of a polar orbiting meteorological satellite high speed data transmission interface circuit based on RS-422 interface circuit form, is characterized in that, comprises in this design circuit:
Transmitting terminal interface chip 26C31 is used for the transmission of data and clock signal; Difference series resistor R1 is used to protect transmitting terminal interface chip 26C31 on the signal positive and negative terminal of transmitting terminal interface chip 26C31;
Receiving terminal interface chip 26C32 is used for the reception of data and clock signal; Power supply anode serial connection diode D at receiving terminal interface chip 26C32 is used to protect receiving terminal interface chip 26C32; Series resistor R2 between the signal anode of diode D and receiving terminal interface chip 26C32; Power supply negative terminal series resistor R4 at receiving terminal interface chip 26C32; Series resistor R3 between the signal positive and negative terminal of receiving terminal interface chip 26C32, said resistance R 2, R3, R4 are used to control the drive current of receiving terminal interface chip 26C32.
2. the method for designing of polar orbiting meteorological satellite high speed data transmission interface circuit as claimed in claim 1; It is characterized in that: said transmitting terminal and receiving terminal are interface type of attachment one to one; That is, riches all the way exports after sending end interface chip 26C31 to connect one road receiving terminal interface chip 26C32.
3. the method for designing of polar orbiting meteorological satellite high speed data transmission interface circuit as claimed in claim 1; It is characterized in that: said transmitting terminal and receiving terminal are for intersecting the backup interface type of attachment; Promptly; Two-way transmitting terminal interface chip 26C31 all connects one road receiving terminal interface chip 26C32 separately, and this two-way receiving terminal interface chip 26C32 exports as one road signal with the back.
4. the method for designing of polar orbiting meteorological satellite high speed data transmission interface circuit as claimed in claim 1; It is characterized in that: said transmitting terminal and receiving terminal are a pair of two interface types of attachment; That is, riches all the way exports as two paths of signals after sending end interface chip 26C31 to connect two-way receiving terminal interface chip 26C32.
5. the method for designing of polar orbiting meteorological satellite high speed data transmission interface circuit as claimed in claim 1; It is characterized in that: said transmitting terminal and receiving terminal are two pairs one interface types of attachment; That is, two-way transmitting terminal interface chip 26C31 exports as one road signal after connecting one road receiving terminal interface chip 26C32.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN2012101190964A CN102684773A (en) | 2012-04-20 | 2012-04-20 | Method for designing high-speed data transmission interfaces of polar-orbit meteorological satellites |
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| CN2012101190964A CN102684773A (en) | 2012-04-20 | 2012-04-20 | Method for designing high-speed data transmission interfaces of polar-orbit meteorological satellites |
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1415971A (en) * | 2001-11-03 | 2003-05-07 | 华为技术有限公司 | Functional test method for measuring fault at single end of difference serial circuit |
| CN101424739A (en) * | 2008-12-05 | 2009-05-06 | 中国电子科技集团公司第十四研究所 | Radar system interface card based on FPGA |
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- 2012-04-20 CN CN2012101190964A patent/CN102684773A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1415971A (en) * | 2001-11-03 | 2003-05-07 | 华为技术有限公司 | Functional test method for measuring fault at single end of difference serial circuit |
| CN101424739A (en) * | 2008-12-05 | 2009-05-06 | 中国电子科技集团公司第十四研究所 | Radar system interface card based on FPGA |
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Application publication date: 20120919 |