CN104836638B - Space optics payload force-disturbance simulation source data transmission format arranges method - Google Patents
Space optics payload force-disturbance simulation source data transmission format arranges method Download PDFInfo
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- CN104836638B CN104836638B CN201510147955.4A CN201510147955A CN104836638B CN 104836638 B CN104836638 B CN 104836638B CN 201510147955 A CN201510147955 A CN 201510147955A CN 104836638 B CN104836638 B CN 104836638B
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L1/00—Arrangements for detecting or preventing errors in the information received
- H04L1/0078—Avoidance of errors by organising the transmitted data in a format specifically designed to deal with errors, e.g. location
- H04L1/0079—Formats for control data
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B10/00—Transmission systems employing electromagnetic waves other than radio-waves, e.g. infrared, visible or ultraviolet light, or employing corpuscular radiation, e.g. quantum communication
- H04B10/11—Arrangements specific to free-space transmission, i.e. transmission through air or vacuum
- H04B10/118—Arrangements specific to free-space transmission, i.e. transmission through air or vacuum specially adapted for satellite communication
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L1/00—Arrangements for detecting or preventing errors in the information received
- H04L1/0001—Systems modifying transmission characteristics according to link quality, e.g. power backoff
- H04L1/0006—Systems modifying transmission characteristics according to link quality, e.g. power backoff by adapting the transmission format
- H04L1/0007—Systems modifying transmission characteristics according to link quality, e.g. power backoff by adapting the transmission format by modifying the frame length
- H04L1/0008—Systems modifying transmission characteristics according to link quality, e.g. power backoff by adapting the transmission format by modifying the frame length by supplementing frame payload, e.g. with padding bits
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Abstract
Space optics payload force-disturbance simulation source data transmission format arranges method, belong to space optics payload to space platform micro-vibration environmental suitability technical field of measurement and test, in order to solve the problems, such as that the data transmission format of multiple degrees of freedom force-disturbance simulation source six roots of sensation force actuator and host computer communication, this method include：The first step arranges wire data type, second step, arrange control parameter, third step arranges power curve of output data, 4th step, the frame head and data length of appointment data transmission frame, the 5th step, arrange channel number, the 6th step, appointment data transmission frame and verification, 7th step, arrange reserved data position, the 8th step, appointment data frame length；This method standardizes data transmission format, and transmission data is divided into two big wire data type of control parameter data and power curve of output data, the data length of every frame is also defined, keeps data transmission relatively reliable and flexible.
Description
Technical field
The present invention relates to a kind of space optics payload force-disturbance simulation source data transmission formats to arrange method, belongs to empty
Between optics payload to space platform micro-vibration environmental suitability technical field of measurement and test.
Background technology
Space optics payload is to be mounted on satellite to set for obtaining the special imaging of interesting target optical information
It is standby.Under the conditions of same application, in order to obtain high quality, high-resolution image, the volume of optics load, clear aperture are more next
It is bigger while also higher and higher to the micro-vibration environmental requirement of the satellite platform residing for it.On satellite platform due to mechanism kinematic,
It trembles caused by solar array is cold and hot, the factors such as moment gyro disturbance cause the satellite platform environment residing for optics payload to be
Micro-vibration, this platform micro-vibration is formed by force-disturbance to high resolution space payload and has become restriction high-resolution
An important factor for space payload image quality.
However the unified micro-vibration ground experiment authentication for high resolution space payload is not yet formed at present
Method, most test methods are facing assembly grade equivalent models, and are also carried with effective on micro-vibration degree of freedom, coupling path
Actually in-orbit environment has prodigious difference to lotus, carries out the ground validation test method towards the whole device micro-vibration of remote sensor and does not appear in the newspapers
Road, ground test experiment are still in the starting stage, and measuring technology and means are limited, especially lack micro- towards whole device suitable for carrying out
The satellite platform micro-vibration source analogy method of vibration test, corresponding space optics payload force-disturbance simulation source data transmission
It is also a technological gap that format, which arranges method,.
Invention content
The present invention is in order to solve the data transmission of multiple degrees of freedom force-disturbance simulation source six roots of sensation force actuator and host computer communication
Format issues provide a kind of space optics payload force-disturbance simulation source data transmission format agreement method.
Space optics payload force-disturbance simulation source data transmission format arranges method, characterized in that including following step
Suddenly：
The first step arranges wire data type, between space optics payload force-disturbance simulation source host computer slave computer
The data of transmission are divided into control parameter data and power curve of output data, and respectively with a byte " 33H ", " 11H " is indicated；
Second step arranges control parameter, and control parameter includes that the proportion adjustment parameter of PID controller accounts for 4 byte wides,
Integral adjustment parameter accounts for 4 byte wides, and differential adjustment parameter accounts for 4 byte wides, the magnitude parameters that sinusoidal force curve generates
2 byte wides are accounted for, the frequency parameter that sinusoidal force curve generates accounts for 2 byte wides, the phase parameter that sinusoidal force curve generates
Account for 2 byte wides, sequence and position of the parameters in order data frame；
Third walks, and arranges power curve of output data, each power curve of output data transmission frames transmits 10 power and exports number
Strong point, each power output data point account for 2 byte wides, firmly transmitted by the 8th the 9th byte representation of curve of output data frame
The block number of power output data where 10 power output data points, sequence and position of each data point in power curve of output data frame
It sets；
4th step, the frame head and data length of appointment data transmission frame, frame head are the first two byte of data transmission frames, point
Not Yong " EBH ", " 90H " indicate, the third byte representation of data length data transmission frames, value be each data transmission frames
The byte number of middle transmission data；
5th step arranges channel number, using the 5th byte of data transmission frames as space optics payload force-disturbance mould
The channel recognition number in quasi- source, to distinguish which force actuator is the data that every frame is transmitted correspond to, " 01H " indicates the 1st channel,
" 02H " indicates that the 2nd channel, " 04H " indicate that the 3rd channel, " 08H " indicate that the 4th channel, " 10H " indicate that the 5th channel, " 20H " indicate
6th channel；
6th step, appointment data transmission frame and verification, the last bytes of data transmission frames be all data of the frame
Low eight of the cumulative sum of byte；
7th step, agreement reserved data position, the 6th the 7th byte of data transmission frames is as the data reserved place per frame, this two
A padding bytes zero, temporary no data meaning；
8th step, appointment data frame length, control parameter data frame totally 26 bytes, wherein data byte are 22, power
Curve of output data frame totally 30 bytes, wherein data byte are 26.
The positive effect of the present invention：The present invention solves space optics payload force-disturbance simulation source host computer slave computer
Between data transmission format agreement problem, data transmission format is standardized, by transmission data be divided into control parameter data and
Two big wire data type of power curve of output data, also defines the data length of every frame, make data transmission it is relatively reliable and
Flexibly.
Description of the drawings
Fig. 1 is the step flow diagram of the method for the present invention.
Specific implementation mode
The present invention is described in further details below in conjunction with the accompanying drawings.
As shown in Figure 1, space optics payload force-disturbance simulation source data transmission format arranges method.This method includes
Following sections：Arrange wire data type 1, agreement control parameter 2, agreement power curve of output data 3, appointment data transmission frame
Frame head and data length 4, agreement channel number 5, appointment data transmission frame and verification 6, agreement reserved data position 7 and about fixed number
According to frame length 8.
This method the specific steps are：
The first step, arranges wire data type, space optics payload force-disturbance simulation source host computer and slave computer it
Between the data transmitted be divided into control parameter data and power curve of output data, indicated respectively with a byte " 33H " and " 11H ".
Second step arranges control parameter, and control parameter includes that the proportion adjustment parameter of PID controller accounts for 4 byte wides,
Integral adjustment parameter accounts for 4 byte wides, and differential adjustment parameter accounts for 4 byte wides, the magnitude parameters that sinusoidal force curve generates
2 byte wides are accounted for, the frequency parameter that sinusoidal force curve generates accounts for 2 byte wides, the phase parameter that sinusoidal force curve generates
Account for 2 byte wides, sequence and position of the parameters in order data frame, as shown in table 1.
Table 1：
Third walks, and arranges power curve of output data, each power curve of output data transmission frames transmits 10 power and exports number
Strong point, each power output data point account for 2 byte wides, firmly curve of output data frame the 8th, transmitted by the 9th byte representation
10 power output data points where power output data block number, sequence of each data point in power curve of output data frame and
Position, as shown in table 2.
Table 2：
4th step, the frame head and data length of appointment data transmission frame, frame head are the first two byte of data transmission frames, point
Not Yong " EBH " and " 90H " indicate, the third byte representation of data length data transmission frames, value be each data transmission
The byte number of transmission data in frame.
5th step arranges channel number, using the 5th byte of data transmission frames as space optics payload force-disturbance mould
The channel recognition number in quasi- source, to distinguish which force actuator is the data that every frame is transmitted correspond to, as shown in table 3, " 01H " table
Show the 1st channel, " 02H " indicates that the 2nd channel, " 04H " indicate that the 3rd channel, " 08H " indicate that the 4th channel, " 10H " indicate that the 5th is logical
Road, " 20H " indicate the 6th channel.
Table 3：
| Coding | Channel number |
| 01H | 1 channel |
| 02H | 2 channels |
| 04H | 3 channels |
| 08H | 4 channels |
| 10H | 5 channels |
| 20H | 6 channels |
6th step, appointment data transmission frame and verification, the last bytes of data transmission frames be all data of the frame
Low eight of the cumulative sum of byte.
7th step, agreement reserved data position, the 6th the 7th byte of data transmission frames is as the data reserved place per frame, this two
A padding bytes zero, temporary no data meaning.
8th step, appointment data frame length, control parameter data frame totally 26 bytes, wherein data byte are 22, power
Curve of output data frame totally 30 bytes, wherein data byte are 26.
Claims (1)
1. space optics payload force-disturbance simulation source data transmission format arranges method, characterized in that include the following steps：
The first step is arranged wire data type, is transmitted between space optics payload force-disturbance simulation source host computer slave computer
Data be divided into control parameter data and power curve of output data, respectively with a byte " 33H ", " 11H " is indicated；
Second step arranges control parameter, and control parameter includes that the proportion adjustment parameter of PID controller accounts for 4 byte wides, integral
Adjustment parameter accounts for 4 byte wides, and differential adjustment parameter accounts for 4 byte wides, and the magnitude parameters that sinusoidal force curve generates account for 2
Byte wide, the frequency parameter that sinusoidal force curve generates account for 2 byte wides, and the phase parameter that sinusoidal force curve generates accounts for 2
Byte wide, sequence and position of the parameters in order data transmission frame；
Third walks, and arranges power curve of output data, each power curve of output data transmission frames transmits 10 power output data points,
Each power output data point accounts for 2 byte wides, firmly transmitted by the 8th the 9th byte representation of curve of output data transmission frames
The block number of power output data where 10 power output data points, sequence of each data point in power curve of output data transmission frames
And position；
4th step, the frame head and data length of appointment data transmission frame, frame head are the first two byte of data transmission frames, are used respectively
" EBH " and " 90H " is indicated, the third byte representation of data length data transmission frames, and value is in each data transmission frames
The byte number of transmission data；
5th step arranges channel number, using the 5th byte of data transmission frames as space optics payload force-disturbance simulation source
Channel recognition number, to distinguish which force actuator is the data that every frame is transmitted correspond to, " 01H " indicate the 1st channel,
" 02H " indicates that the 2nd channel, " 04H " indicate that the 3rd channel, " 08H " indicate that the 4th channel, " 10H " indicate that the 5th channel, " 20H " indicate
6th channel；
6th step, appointment data transmission frame and verification, the last bytes of data transmission frames be all data bytes of the frame
Low eight of cumulative sum；
7th step, agreement reserved data position, the 6th the 7th byte of data transmission frames is as the reserved data position per frame, two words
Section filling zero, temporary no data meaning；
8th step, appointment data transmission frame length, control parameter data transmission frames totally 26 bytes, wherein data byte are 22
A, power curve of output data transmission frames totally 30 bytes, wherein data byte are 26.
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| CN103678498A (en) * | 2013-11-18 | 2014-03-26 | 航天东方红卫星有限公司 | General analysis method for effective load data of satellites |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102007050941A1 (en) * | 2007-10-23 | 2009-04-30 | Phoenix Contact Gmbh & Co. Kg | Method for transmitting data in a communications network, transmitting and receiving device for a communications network |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102577313A (en) * | 2009-09-01 | 2012-07-11 | 信息控制公司 | Methods and systems for communication protocol for distributed asset management |
| CN103678498A (en) * | 2013-11-18 | 2014-03-26 | 航天东方红卫星有限公司 | General analysis method for effective load data of satellites |
Non-Patent Citations (2)
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| 卫星飞轮微振动隔离方法与技术研究;魏展基;《中国优秀硕士学位论文全文数据库工程科技Ⅱ辑》;20141115;全文 * |
| 空间通信中可变长数据帧协议与变速率信息传输技术的研究;郝营;《中国优秀硕士学位论文全文数据库信息科技辑》;20100615(第6期);全文 * |
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